COMBUSTOR WITH A DILUTION PASSAGE

TECHNICAL FIELD

The present subject matter relates generally to a combustor, and more specifically to a combustor having a liner, and a dilution passage extending through the liner.

BACKGROUND

Gas turbine engines are driven by a flow of combustion gases passing through the engine to rotate a multitude of turbine blades. A combustor can be provided within the gas turbine engine and is fluidly coupled with a turbine into which the combusted gases flow.

Hydrocarbon fuels are commonly used in the combustor of a gas turbine engine.

Generally, air and fuel are fed separately to the combustor, until they are mixed, and the mixture is combusted to produce hot combustion gas. The combustion gas is then fed to a turbine where it rotates the turbine to produce power. By-products of the hydrocarbon fuel combustion typically include nitrogen oxide and nitrogen dioxide (collectively called NOx), carbon monoxide (CO), unburned hydrocarbon (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides, including oxides of sulfur (e.g., SO₂and SO₃).

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:

FIG. 1 is a schematic of a gas turbine engine.

FIG. 2 is a schematic of a cross-section view taken along line II-II of FIG. 1 of a combustion section of the gas turbine engine, the combustion section have a combustor centerline.

FIG. 3 is a schematic of a side cross-sectional view taken along line III-III of FIG. 2 of a combustor in the combustion section having a liner, a casing, a compressed air passageway formed between the liner and the casing, a dilution passage formed along the liner, and a baffle provided within the compressed air passageway and occluding a compressed airflow to the dilution passage.

FIG. 4 is a schematic side cross-sectional view of the baffle taken along line IV-IV of FIG. 3, further illustrating the baffle in an open position.

FIG. 5 is a schematic side cross-sectional of the baffle of FIG. 3, further illustrating the baffle in a closed position.

FIG. 6 is a schematic transverse cross-sectional view of the combustor taken along line VI-VI of FIG. 3, further illustrating two baffles circumferentially extending across respective portions of the liner.

FIG. 7 is a schematic side cross-sectional view of an exemplary baffle for a combustor suitable for use as the combustor of FIG. 3, the baffle being movable along the axial direction of a mean centerline of the combustor.

FIG. 8 is a schematic side cross-sectional view of an exemplary baffle for a combustor suitable for use as the combustor of FIG. 3, the baffle being radially inclined at a radial baffle angle with respect to a mean centerline of the combustor.

FIG. 9 is a schematic top-down view of an exemplary baffle for a combustor suitable for use as the combustor of FIG. 3, the baffle occluding the compressed airflow to a set of axially-spaced dilution passages and including a circumferential baffle angle with respect to a mean centerline of the combustor.

FIG. 10 is a schematic top-down view of an exemplary baffle for a combustor suitable for use as the combustor of FIG. 3, the including a circumferential baffle angle with respect to a mean centerline of the combustor.

FIG. 11 is a schematic side cross-sectional view of an exemplary baffle for a combustor suitable for use as the combustor of FIG. 3, the combustor including a first channel and a second channel, with the baffle being pivotable about a static arm to occlude the compressed airflow to the first channel, the baffle being in a first position.

FIG. 12 is a schematic side cross-sectional view of the exemplary baffle of FIG. 11, the baffle being in a second position.

FIG. 13 is a schematic side cross-sectional view of an exemplary baffle for a combustor suitable for use as the combustor of FIG. 3, the combustor including a first channel and a second channel, with the baffle being pivotable about a static arm to occlude the compressed airflow to the first channel or the second channel.

FIG. 14 is a schematic side cross-sectional view of an exemplary set of baffles within a combustor suitable for as the combustor of FIG. 3, the two baffles being dependently movable.

FIG. 15 is a schematic side cross-sectional view of an exemplary set of baffles within a combustor suitable for as the combustor of FIG. 3, the two baffles being independently movable.

FIG. 16 is a schematic side cross-sectional view of an exemplary set of baffles within a combustor suitable for as the combustor of FIG. 3, the combustor including a mean centerline that is non-parallel to the combustor centerline.

FIG. 17 is a schematic transverse cross-sectional view of an exemplary combustor suitable for use as the combustor of FIG. 3, further including two baffles provided at varying radial heights from a mean centerline of the combustor.

DETAILED DESCRIPTION

Aspects of the disclosure described herein are directed to a combustor. The combustor includes a combustion chamber at least partially defined by a dome wall, a casing, an inner liner and an outer liner. A compressed air passageway is formed between the casing, the inner liner and the outer liner. A set of dilution passages extend through at least one of the inner liner or the outer liner fluidly coupling the compressed air passageway to the combustion chamber. A baffle is provided in a portion of the compressed air passage. The baffle is movable to occlude a compressed air within the compressed air passageway to at least a portion of the set of dilution passages. As used herein, the term occlude is defined as to stop, limit, or otherwise constrict a flow of air from a first passage from entering a second passage.

For purposes of illustration, the present disclosure will be described with respect to a gas turbine engine. It will be understood, however, that aspects of the disclosure described herein are not so limited and that a combustor as described herein can be implemented in engines, including but not limited to turbojet, turboprop, turboshaft, and turbofan engines. Aspects of the disclosure discussed herein may have general applicability within non-aircraft engines having a combustor, such as other mobile applications and non-mobile industrial, commercial, and residential applications.

The word “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other implementations. Additionally, unless specifically identified otherwise, all embodiments described herein should be considered exemplary.

As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

The terms “forward” and “aft” refer to relative positions within a gas turbine engine or vehicle, and refer to the normal operational attitude of the gas turbine engine or vehicle. For example, with regard to a gas turbine engine, forward refers to a position closer to an engine inlet and aft refers to a position closer to an engine nozzle or exhaust.

As used herein, the term “upstream” refers to a direction that is opposite the fluid flow direction, and the term “downstream” refers to a direction that is in the same direction as the fluid flow. The term “fore” or “forward” means in front of something and “aft” or “rearward” means behind something. For example, when used in terms of fluid flow, fore/forward can mean upstream and aft/rearward can mean downstream.

The term “fluid” may be a gas or a liquid. The term “fluid communication” means that a fluid is capable of making the connection between the areas specified.

Additionally, as used herein, the terms “radial” or “radially” refer to a direction away from a common center. For example, in the overall context of a gas turbine engine, radial refers to a direction along a ray extending between a center longitudinal axis of the engine and an outer engine circumference.

All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of aspects of the disclosure described herein. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and can include intermediate structural elements between a collection of elements and relative movement between elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and in fixed relation to one another. The exemplary drawings are for purposes of illustration only and the dimensions, positions, order and relative sizes reflected in the drawings attached hereto can vary.

The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise. Furthermore, as used herein, the term “set” or a “set” of elements can be any number of elements, including only one.

Approximating language, as used herein throughout the specification and claims, is applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, “generally”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and/or systems. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and/or systems. For example, the approximating language may refer to being within a 1, 2, 4, 5, 10, 15, or 20 percent margin in either individual values, range(s) of values and/or endpoints defining range(s) of values. Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

FIG. 1 is a schematic view of a gas turbine engine 10. As a non-limiting example, the gas turbine engine 10 can be used within an aircraft. The gas turbine engine 10 can include, at least, a compressor section 12, a combustion section 14, and a turbine section 16 in serial flow arrangement. A drive shaft 18 rotationally couples the compressor and turbine sections 12, 16, such that rotation of one affects the rotation of the other, and defines a rotational axis or engine centerline 21 for the gas turbine engine 10.

The compressor section 12 can include a low-pressure (LP) compressor 22, and a high-pressure (HP) compressor 24 serially fluidly coupled to one another. The turbine section 16 can include an LP turbine 26, and an HP turbine 28 serially fluidly coupled to one another. The drive shaft 18 can operatively couple the LP compressor 22, the HP compressor 24, the LP turbine 26 and the HP turbine 28 together. Alternatively, the drive shaft 18 can include an LP drive shaft (not illustrated) and an HP drive shaft (not illustrated). The LP drive shaft can couple the LP compressor 22 to the LP turbine 26, and the HP drive shaft can couple the HP compressor 24 to the HP turbine 28. An LP spool can be defined as the combination of the LP compressor 22, the LP turbine 26, and the LP drive shaft such that the rotation of the LP turbine 26 can apply a driving force to the LP drive shaft, which in turn can rotate the LP compressor 22. An HP spool can be defined as the combination of the HP compressor 24, the HP turbine 28, and the HP drive shaft such that the rotation of the HP turbine 28 can apply a driving force to the HP drive shaft which in turn can rotate the HP compressor 24.

The compressor section 12 can include a plurality of axially spaced stages. Each stage includes a set of circumferentially-spaced rotating blades and a set of circumferentially-spaced stationary vanes. The compressor blades for a stage of the compressor section 12 can be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the compressor section 12 can be mounted to a casing which can extend circumferentially about the gas turbine engine 10. It will be appreciated that the representation of the compressor section 12 is merely schematic and that there can be any number of stages. Further, it is contemplated, that there can be any other number of components within the compressor section 12.

Similar to the compressor section 12, the turbine section 16 can include a plurality of axially spaced stages, with each stage having a set of circumferentially-spaced, rotating blades and a set of circumferentially-spaced, stationary vanes. The turbine blades for a stage of the turbine section 16 can be mounted to a disk which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the turbine section can be mounted to the casing in a circumferential manner. It is noted that there can be any number of blades, vanes and turbine stages as the illustrated turbine section is merely a schematic representation. Further, it is contemplated, that there can be any other number of components within the turbine section 16.

The combustion section 14 can be provided serially between the compressor section 12 and the turbine section 16. The combustion section 14 can be fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 can be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and to the HP turbine 28 at a downstream end of the combustion section 14.

During operation of the gas turbine engine 10, ambient or atmospheric air is drawn into the compressor section 12 via a fan (not illustrated) upstream of the compressor section 12, where the air is compressed defining a pressurized air. The pressurized air can then flow into the combustion section 14 where the pressurized air is mixed with fuel and ignited, thereby generating combustion gases. Some work is extracted from these combustion gases by the HP turbine 28, which drives the HP compressor 24. The combustion gases are discharged into the LP turbine 26, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the gas turbine engine 10 via an exhaust section (not illustrated) downstream of the turbine section 16. The driving of the LP turbine 26 drives the LP spool to rotate the fan (not illustrated) and the LP compressor 22. The pressurized airflow and the combustion gases can together define a working airflow that flows through the fan, compressor section 12, combustion section 14, and turbine section 16 of the gas turbine engine 10.

FIG. 2 depicts a cross-section view of the combustion section 14 taken along line II-II of FIG. 1. The combustion section 14 includes a combustor 80 having a set of fuel cups 76 disposed around a combustor centerline 36. The combustor centerline 36 can be in-line with, offset from, parallel to, or non-parallel to the engine centerline 21 of the gas turbine engine 10 (FIG. 1). The combustor centerline 36 can be a centerline for an entirety of the combustion section 14, a single combustor, or a set of combustors that are arranged about the combustor centerline 36.

The combustor 80 can have a can, can-annular, or annular arrangement depending on the type of engine in which the combustor 80 is located. In a non-limiting example, an annular arrangement is illustrated and disposed within a casing 78. The combustor 80 is defined by a liner 82 including an outer liner 82a and an inner liner 82b concentric with respect to each other and annular about the combustor centerline 36. The combustor 80 includes a dome assembly 84 including a dome wall 90. The dome wall 90, the outer liner 82a and the inner liner 82b, together, at least partially define a combustion chamber 86. The combustion chamber 86 is annular about the combustor centerline 36.

At least one fuel cup 76, illustrated as multiple fuel injectors annularly arranged about the combustor centerline 36, is fluidly coupled to the combustion chamber 86. A compressed air passageway 88 can be defined at least in part by both the liner 82 and the casing 78.

The at least one fuel cup 76 is included within a plurality of fuel cups 76. Each fuel cup 76 can include a fuel cup centerline 34 that extends into the page. Each fuel cup centerline 34 can be arranged along a circumferential line 70. Alternatively, one or more fuel cups 76 can be offset from the circumferential line 70. Additionally, the fuel cups 76 can be arranged such that the fuel cup centerlines 34 form a pattern relative to, but not necessarily on, the circumferential line 70.

FIG. 3 depicts a cross-section view taken along line III-III of FIG. 2 illustrating the combustion section 14. The fuel cup 76 can be coupled to and disposed within the dome assembly 84. The fuel cup 76 can include a flare cone 104 and a swirler 112. The flare cone 104 includes an outlet 96 of the fuel cup 76 directly fluidly coupled to the combustion chamber 86. The fuel cup 76 is fluidly coupled to a fuel inlet 98 via a linear passageway 100.

Both the outer and inner liners 82a, 82b have an outer surface 106 and an inner surface 108. The inner surface 108 at least partially defining the combustion chamber 86. The liner 82 can be made of one continuous monolithic portion or be multiple monolithic portions assembled together to define the outer and inner liners 82a, 82b. By way of non-limiting example, the outer surface 106 can define a first piece of the liner 82 while the inner surface 108 can define a second piece of the liner 82 that when assembled together form the liner 82. It is further contemplated that the liner 82 can be any type of liner 82, including but not limited to a single wall or a double walled liner or a tile liner. An ignitor 110 can be provided at the liner 82 and fluidly coupled to the combustion chamber 86, at any location.

When viewed from an axial plane extending from the combustor centerline 36 (FIG. 2) and passing through a center point of the fuel cup 76, a mean centerline 124, lying in the axial plane, extends through the combustion chamber 86 equidistant between the inner liner 82b and the outer liner 82a. The mean centerline 124 can begin at or be radially offset from the fuel cup centerline 34 (FIG. 2) at the outlet 96.

The compressed air passageway 88 is formed between the outer surface 106 of the outer liner 82a and the inner liner 82b, and opposing portions of the casing 78. A first set of dilution passages 92 can extend through the dome wall 90 and exhaust to the combustion chamber 86. A second set of dilution passages 120 can extend through at least one of the inner liner 82b and the outer liner 82a. Each dilution passage of the second set of dilution passages 120 includes an inlet 126 provided on the outer surface 106 and a dilution hole 122 provided on the inner surface 108. The second set of dilution passages 120 fluidly couple the compressed air passageway 88 to the combustion chamber 86

A set of baffles 130 is provided within a portion of the compressed air passageway 88 axially aligned with at least a portion of the second set of dilution passages 120. Each baffle of the set of baffles 130 are operably coupled to an arm 132. The arm 132 is operably coupled to an actuator 136. As used herein, the actuator 136 can be any suitable device used to translate the arm in at least one direction. As a non-limiting example, the actuator 136 can be an AC or DC motor, a DC motor, a pneumatic pump, an engine, a hydraulic pump, an electromagnetic actuator, a piezoelectric motor, or an electromechanical motor. While two baffles are illustrated, it will be appreciated that the set of baffles 130 can include any number of one or more baffles. Further, while illustrated as being provided radially outward from both of the inner liner 82b and the outer liner 82a, with respect to the mean centerline 124, it will be appreciated that the set of baffles 130 can be provided radially outward from a single liner of the inner liner 82b or the outer liner 82a.

During operation, a compressed airflow (C) can flow from the compressor section 12 (FIG. 1) to the combustor 80 through the dome assembly 84. The compressed airflow (C) is fed to the fuel cup 76 via the swirler 112 as a swirler airflow (S). A flow of fuel (F) is fed to the fuel cup 76 via the fuel inlet 98 and the linear passageway 100. The swirler airflow (S) and the flow of fuel (F) are mixed at the flare cone 104 and fed to the combustion chamber 86 as a fuel/air mixture. The ignitor 110 can ignite the fuel/air mixture to define a flame within the combustion chamber 86, which generates a combustion gas (G). While shown as starting axially downstream of the outlet 96, it will be appreciated that the fuel/air mixture can be ignited at or near the outlet 96.

The compressed airflow (C) is further fed to the first set of dilution passages 92 as a first dilution airflow (D1) and through the compressed air passageway 88 to the second set of dilution passages 120 as a second dilution airflow (D2). The first dilution airflow (D1) is used to direct and shape a flame, while the second dilution airflow (D2) is used to further shape and direct the combustion gas (G) or the flame. It is contemplated that the compressed airflow (C) fed through the second set of dilution passages 120 can make up greater than or equal to 20% and less than or equal to 80% of the total compressed airflow (C) that is fed to the combustor 80. As a non-limiting example, the compressed airflow (C) fed through the second set of dilution passages 120 can make up greater than or equal to 30% and less than or equal to 50% of the total compressed airflow (C) that is fed to the combustor 80.

At least a portion of the compressed airflow (C) in the compressed air passageway 88 can continue past the second set of dilution passages 120 and to downstream portions of the gas turbine engine 10 (FIG. 1) to define a bypass compressed airflow (Cb). The bypass compressed airflow (Cb) can be used for any suitable purpose such as, but not limited to, cooling.

FIG. 4 is a schematic side cross-sectional view of the baffle 130 taken along line IV-IV of FIG. 3. The baffle 130, as described herein, is provided within the compressed air passageway 88 confronting the liner 82. It will be appreciated that the liner 82 can be any one of the outer liner 82a (FIG. 3) or the inner liner 82b (FIG. 3). Further, the second set of dilution passages 120 will hereinafter be referred to as the set of dilution passages 120.

The baffle 130 axially overlies at least a portion of the dilution passage 120. As a non-limiting example, the baffle 130 axially overlies the inlet 126 of the dilution passage 120. The baffle 130 is movable, via the arm 132. The baffle 130 has a range of movement that has a degree of freedom in at least one of the radial direction or an axial direction. As a non-limiting example, the degree of freedom of the baffle 130 is along a radial plane of movement 134.

The baffle 130, as illustrated, is in a first position where the second dilution airflow (D2) is free to flow into the dilution passage 120 through the inlet 126. The baffle 130 can be moved along the radial plane of movement 134 a maximum radial distance from the outer surface 106 of the liner 82. As a non-limiting example, the maximum radial distance can be an instance where the baffle 130 confronts and contacts a respective portion of the casing 78 (FIG. 3). The baffle 130 can further be sized such that it sits flush against a respective portion the liner 82 or the casing 78.

FIG. 5 is a schematic side cross-sectional view of the baffle 130 of FIG. 3 in a second position. The baffle 130, as illustrated, is in the second position where the second dilution airflow (D2) is impeded or otherwise stopped from flowing into the dilution passage 120. The baffle 130 is moveable between the first position (FIG. 4) and the second position to effectively occlude the compressed airflow (C) from the inlet 126 of the dilution passage 120. It will be appreciated that in the first position, the compressed airflow (C) is fully occluded and when the baffle 130 is in the second position, the compressed airflow |(C) can be less than 100% and greater than or equal to 0% occluded. When the baffle 130 partially or fully occludes the compressed airflow (C) from the dilution passage 120, the compressed airflow (C) that would flow into the dilution passage 120 if the dilution passage 120 were not occluded can instead flow to a downstream portion of the gas turbine engine (FIG. 1) as the bypass compressed airflow (Cb). In other words, the positioning of the baffle 130 can be used to tailor the amount of the second dilution airflow (D2) and the bypass compressed airflow (Cb) that flows through the combustor 80 (FIG. 3).

It is contemplated that the positioning of the baffle 130 can further be used to tailor at least one flow characteristic of the second dilution airflow (D2). As a non-limiting example, the baffle 130 can be positioned with respect to the inlet 126 such that the baffle 130 acts as a nozzle for the second dilution airflow (D2) being fed to the inlet 126. When acting as a nozzle, the baffle 130 can accelerate and pressurize the second dilution airflow (D2).

The control of the amount and the flow characteristics of the second dilution airflow (D2) flowing through the dilution passage 120 by the baffle 130 can be used for flame-shaping purposes. During operation of the combustor 80, an ignited mixture of fuel (F) and the first dilution airflow (D1) can generate a flame or otherwise the combustion gases (G). The second dilution airflow (D2) is used to affect how the flame or the combustion gases flow through the combustion chamber 86. As a non-limiting example, a faster and larger volume of the second dilution airflow (D2) can be used to penetrate into the combustion chamber 86 and effectively reduce the footprint of the flame or the combustion gases (G) within the combustion chamber 86. Conversely, if the baffle 130 is moved to close off the inlet 126 such that no second dilution airflow (D2) flows into the combustion chamber 86, the flame or the combustion gases (G) will have more room to expand and thus have a larger footprint.

The shaping of the flame or the combustion gases (G) is hereinafter referred to as flame shaping. It is contemplated that flame shaping through the presence or non-presence of the second dilution airflow (D2) by the selective movement of the baffle 130 can be used to tailor the footprint or profile of the flame within the combustion chamber 86. The flame shaping can further be used to tailor a temperature distribution at the outlet of the combustion chamber 86. As a non-limiting example, a uniform temperature distribution at the outlet can ensure that the gas turbine engine 10 is uniformly thermally loaded downstream of the combustion section 14, thus increasing the efficiency and lifespan of the gas turbine engine 10 (FIG. 1).

The positioning of the baffle 130 can further be dependent on the operational state of the gas turbine engine 10 (FIG. 1). For example, it has been found that during a relight condition (e.g., during initial ignition or restart ignition of the fuel/air mixture exiting the fuel cup 76 of FIG. 3), the baffle 130 can fully or partially cover the set of dilution passages 120 such that a maximum amount of compressed air (C) (FIG. 3) flows into the combustion chamber 86 as the first dilution airflow (D1), into the swirler 112 as the swirler airflow (S) or otherwise to a downstream portion of the gas turbine engine 10 as the bypass compressed airflow (Cb). It has been found that maximizing, for example, the swirler airflow (S) and the first dilution airflow (D1) can help with initial flame propagation and shaping to ensure proper ignition of the gas turbine engine 10. Further, maximizing the amount of compressed air (C) being fed to the swirler 112 by closing the baffle 130, increases the flow through the swirler 112 which increases the pressure drop across the swirler 112 and a velocity of the flow exiting the swirler 112 at the outlet 96. Once ignited, it may be desirable to have further flame shaping through use of the set of dilution passages 120. As such, the baffle 130 can be moved to partially uncover or fully uncover the inlets 126, thus allowing the second dilution airflow (D2) to flow into the combustion chamber 86.

The combustor 80 shown of FIG. 3 is well suited for the use of a hydrogen-containing gas as the fuel because it helps contain the faster moving flame front associated with hydrogen fuel, as compared to traditional hydrocarbon fuels. However, the combustor 80 can be used with traditional hydrocarbon fuels.

It has been found that use of the baffle 130 is especially advantageous in instances where the fuel used in the combustion section 14 is a hydrogen-containing fuel. Hydrogen-containing fuel has a higher calorific value than conventional fuels (e.g., fuels using carbons), thus the flame or combustion gases (G) generated with hydrogen-containing fuels is hotter than a flame or combustion gases that are generated with conventional fuels. As such, directing the flame away from various portions of the combustion section 14 (e.g., the inner liner 82b and the outer liner 82a) through the second dilution airflow (D2) ensures that the heat from the flame does not damage portions of the combustion section 14 that cannot withstand the heat of the flame. Further, the flame generated by the hydrogen-containing fuel has a higher velocity than a flame generated by a conventional fuel. The higher velocity, in turn, means that the flame tends to want to keep its shape, which can result in a non-uniform flame and temperature distribution at the outlet of the combustor 80. The baffle 130 is used to ensure that the flames or combustion gases (G) have a uniform temperature and flame distribution at the outlet of the combustion chamber 86.

With reference to the relight condition (e.g., closing the baffle 130), increasing the velocity of the flow exiting the outlet 96 of the fuel cup 76 is especially advantageous when using hydrogen as a fuel. It has been found that the increase in the velocity of the hydrogen fuel and air mixture at the outlet 96, in turn, reduces chances of flashback and flame holding on the fuel cup 76 and the dome wall 90.

FIG. 6 is a schematic transverse cross-sectional view of the combustor 80 taken along line VI-VI of FIG. 3. The set of baffles 130 can extend circumferentially continuously about or be circumferentially segmented about the mean centerline 124 (FIG. 3) or the combustor centerline 36.

The set of baffles 130 can include two or more circumferentially adjacent baffles 130. Each baffle of the two or more circumferentially adjacent baffles 130 can be independently movable via a respective arm 132 and further overlay a respective portion of the set of dilution passages 120. Each arm 132 can be coupled to a respective actuator 136 (FIG. 3) or to a single common actuator 136.

Each baffle of the two or more circumferentially adjacent baffles 130 can further correspond to any number of one or more fuel cups 76. As a non-limiting example, each baffle of the two or more circumferentially adjacent baffles 130 can extend circumferentially across two respective fuel cups 76.

The independent movement of the baffles of the two or more circumferentially adjacent baffles 130 allows for further flame shaping by controlling the location where the second dilution airflow (D2) (FIG. 3) flows into the combustion chamber 86.

FIG. 7 is a schematic side cross-sectional view of an exemplary baffle 230 provided within a combustor 280 suitable for use within the combustor 80 of FIG. 3. The combustor 280 is similar to the combustor 80, therefore, like parts will be identified by like numerals increased to the 200 series with it being understood that the description of the combustor 80 applies to the combustor 280 unless noted otherwise.

The combustor 280 includes a liner 282 with an outer surface 206 and an inner surface 208. A dilution passage 220 extends through the liner 282 between an inlet 226 provided on the outer surface 206 and a dilution hole 222 provided on the inner surface 208. The inner surface 208 confronts and at least partially defines a combustion chamber 286. A mean centerline 224 extends through the combustion chamber 286. The outer surface 206 at least partially defines a compressed air passageway 288. The baffle 230 is provided within a portion of the compressed air passageway 288. The baffle 230 is movable within the compressed air passageway 288 via an arm 232.

The baffle 230 is similar to the baffle 130 (FIG. 3), as the baffle 230 occludes the second dilution airflow (D2) (FIG. 3) from the inlet 226 of the dilution passage 220. The baffle 230, however, has a range of movement that has a degree of freedom in at least one of the radial direction or an axial direction. As a non-limiting example, the degree of freedom of the baffle 130 is along an axial plane of movement 238 rather than the radial plane of movement 134 (FIG. 4). It is contemplated that the baffle 230, therefore, can be slidably moved over the inlet 226 to fully cover, partially cover, or fully uncover the inlet 226. In the instance where the inlet 226 is partially covered, the baffle 230 acts as a nozzle for the compressed airflow (C) (FIG. 3) flowing into the inlet 226.

It is contemplated that the set of dilution passages 220 can include any number of one or more axially downstream dilution passages 240. The baffle 230 can be sized to partially cover, fully cover, or fully uncover the one or more axially downstream dilution passages 240. The baffle 230 is movable such that the axially downstream dilution passages 240 and the axially upstream dilution passages have varying degrees of occlusion. It will be appreciated that the baffle 230 can be sized such that the baffle 230 can simultaneously fully cover, partially cover, or fully uncover all dilution passages of the set of dilution passages 220 including the one or more axially downstream dilution passages 240.

The selective occlusion of the compressed airflow to the set of dilution passages 220 optionally including the axially downstream dilution passage 240 can be used to further tailor the flame shaping. As a non-limiting example, fully uncovering or partially uncovering the axially downstream dilution passages 240 can be used to further shape the flame or combustion gases (G) downstream of the axially forward dilution passages of the set of dilution passages 220.

As a non-limiting example, blocking the upstream dilution passages 220 and allowing the second dilution airflow (D2) to flow through the axially downstream dilution passage 240 can allow for the flame or combustion gases (G) to further expand radially outward from the mean centerline 224, hereinafter referred to as an increase in flame volume. The increase in flame volume, in turn, achieves better flame stability. It is contemplated that opening the axially downstream dilution passages 240, during relight, can allow for a more stable flame and thus increase the efficiency of the combustor 280 during startup of the combustor 280. It has been further found that varying the occlusion of the set of dilution passages 220 and the set of axially downstream dilution passages 240 can further limit the amount of emissions generated by the combustion process.

FIG. 8 is a schematic side cross-sectional view of an exemplary baffle 330 provided within a combustor 380 suitable for use within the combustor 80 of FIG. 3. The combustor 380 is similar to the combustor 80, 280, therefore, like parts will be identified by like numerals increased to the 300 series with it being understood that the description of the combustor 80, 280 applies to the combustor 380 unless noted otherwise.

The combustor 380 includes a liner 382 with an outer surface 306 and an inner surface 308. A dilution passage 320 extends through the liner 382 between an inlet 326 provided on the outer surface 306 and a dilution hole 322 provided on the inner surface 308. The inner surface 308 confronts and at least partially defines a combustion chamber 386. A mean centerline 324 extends through the combustion chamber 386. The outer surface 306 at least partially defines a compressed air passageway 388. The baffle 330 is provided within a portion of the compressed air passageway 388. The baffle 330 is movable within the compressed air passageway 388 via an arm 332. The baffle 330 has a range of movement that has a degree of freedom in at least one of the radial direction or an axial direction.

The baffle 330 is similar to the baffle 130, 230 as the baffle 330 occludes the second dilution airflow (D2) (FIG. 3) from the inlet 326 of the dilution passage 320. The baffle 330, however, includes a major body axis 350 extending at a radial baffle angle 346 with respect to a projection 348 of the mean centerline 324. In other words, the baffle 330 is radially inclined with respect to the mean centerline 324. The radial baffle angle 346 can be any suitable size. As a non-limiting example, the radial baffle angle 346 can have an absolute value of greater than or equal to 0 degrees and less than or equal to 80 degrees.

The inclination of the baffle 330 is used to funnel the compressed airflow (C) into the inlet 326. The inclination of the baffle 330 can further be used as a nozzle to accelerate and pressurize the compressed airflow (C) prior to it entering the inlet 326.

FIG. 9 is a schematic top-down view of an exemplary baffle 430 provided within a combustor 480 suitable for use within the combustor 80 of FIG. 4. The combustor 480 is similar to the combustor 80, 280, 380, therefore, like parts will be identified by like numerals increased to the 400 series with it being understood that the description of the combustor 80, 280, 380 applies to the combustor 480 unless noted otherwise.

The combustor 480 includes a liner 482 with an outer surface 406. A dilution passage 420 extends through the liner 482 from an inlet 426 provided on the outer surface 406. The liner 482 confronts and at least partially defines a combustion chamber (not illustrated, e.g., the combustion chamber 86 of FIG. 3). A mean centerline, illustrated as a projection 448, extends through the combustion chamber. The outer surface 406 at least partially defines a compressed air passageway 488. The baffle 430 is provided within a portion of the compressed air passageway 488. The baffle 430 is movable within the compressed air passageway 488 via an arm 432. The baffle 430 has a range of movement that has a degree of freedom in at least one of the radial direction or an axial direction.

The baffle 430 is similar to the baffle 130, 230, 330 in that the baffle 430 occludes a compressed airflow (e.g., the compressed airflow (C) of FIG. 3) from the inlet 426. The baffle 430, however, includes a major body axis 450 forming a circumferential baffle angle 460 with respect to the projection 448 of the mean centerline. The circumferential baffle angle 460 can be any suitable angle. As a non-limiting example, the circumferential baffle angle 460 can have an absolute value of greater than or equal to 0 degrees and less than or equal to 90 degrees. As a non-limiting example, the circumferential baffle angle can have an absolute value of less than 90 degrees.

The set of dilution passages 420 include a series of axially spaced dilutions passages. Each dilution passage of the set of dilution passages 420 includes a dilution passage centerline (e.g., the dilution passage centerline 34 of FIG. 2) that intersects the inlet 426 at a center point 444. The set of dilution passages 420 can be provided along a line 462 that extends between each consecutive center point 444 of the set of dilution passages 420. The major body axis 450 can correspond to or otherwise be parallel to the line 462. As such, the baffle 430 can be moved to cover, partially uncover, or fully uncover all dilution passages of the set of dilution passages 420 at once. It will be appreciated that the line 462, and therefore the major body axis 450, can be linear or non-linear. As such, it will be appreciated that the baffle 430 can be curved or non-curved.

FIG. 10 is a schematic top-down view of an exemplary baffle 530 provided within a combustor 580 suitable for use within the combustor 80 of FIG. 5. The combustor 580 is similar to the combustor 80, 280, 380, 480, therefore, like parts will be identified by like numerals increased to the 500 series with it being understood that the description of the combustor 80, 280, 380, 480 applies to the combustor 580 unless noted otherwise.

The combustor 580 includes a liner 582 with an outer surface 506. A dilution passage 520 extends through the liner 582 from an inlet 526 provided on the outer surface. The liner 582 confronts and at least partially defines a combustion chamber (not illustrated, e.g., the combustion chamber 86 of FIG. 3). A mean centerline, illustrated as a projection 548, extends through the combustion chamber. The outer surface 506 at least partially defines a compressed air passageway 588. The baffle 530 is provided within a portion of the compressed air passageway 588. The baffle 530 is movable within the compressed air passageway 588 via an arm 532. The baffle 530 has a range of movement that has a degree of freedom in at least one of the radial direction or an axial direction.

The baffle 530 is similar to the baffle 430 in that it includes a major body axis 550 that forms a circumferential baffle angle 560 with respect to the projection 548. The difference, however, is that the set of dilution passages 520 are circumferentially spaced along a line 562 that is perpendicular to the projection 548, and extends through a center point 544 of each dilution passage 520. The major body axis 550 is non-parallel to the line 562. As such, the amount of occlusion is non-constant between circumferentially adjacent dilution passages when the baffle 530 is moved over a respective dilution passage 520.

The baffle 530 can further be movable, via the arm 532, about a rotational axis (Rax). In other words, the size of the circumferential baffle angle 560 can be varied by rotating the baffle 530 about the rotational axis (Rax).

During operation the baffle 530 can be used to selectively fully occlude, partially occlude or not occlude (e.g., fully open) at least one of the dilution passages of the set of dilution passages 520 that are in a circumferential row. As a non-limiting example, the baffle 530 can fully occlude a first dilution passage while leaving a second dilution passage, circumferentially adjacent the first dilution passage not occluded or partially occluded. It is contemplated that providing differing amounts of occlusion along the set of dilution passages 520 arranged in the circumferential row can allow for increased temperature control of the flame or combustion gases (G) within the combustion chamber. As a non-limiting example, if a higher flame temperature is measured or expected to be present around the second dilution passage rather than the first dilution passage, the baffle 530 can be moved to direct compressed air through the second dilution passage to effectively push away from the liner 582 or otherwise cool the hot portions of the flame. The cooling of the hotter regions of the flame, in turns, results in a uniform temperature distribution at the outlet of the combustor 580. This ultimately reduces the emissions and achieves a better flame profile at the outlet of the combustor 580.

In instances where the baffle 530 is movable about the rotational axis (Rax), the circumferential baffle angle 560 can be varied to change the degree of occlusion of each dilution passage of the set of dilution passages 520. As a non-limiting example, if it is desired to cover all dilution passages of the set of dilution passages 520, the arm 532 can move the baffle 530 such that the major body axis 550 is parallel to the line 562.

FIG. 11 is a schematic side cross-sectional view of an exemplary baffle 630 provided within a combustor 680 suitable for use within the combustor 80 of FIG. 3. The combustor 680 is similar to the combustor 80, 280, 380, 480, 580, therefore, like parts will be identified by like numerals increased to the 600 series with it being understood that the description of the combustor 80, 280, 380, 480, 580 applies to the combustor 680 unless noted otherwise.

The combustor 680 includes a casing 678 and a liner 682 with an outer surface 606 and an inner surface 608. A dilution passage 620 extends through the liner 682 between an inlet 626 provided on the outer surface 606 and a dilution hole 622 provided on the inner surface 608. The inner surface 608 confronts and at least partially defines a combustion chamber 686. A mean centerline 624 extends through the combustion chamber 686. The outer surface 606 at least partially defines a compressed air passageway 688. The baffle 630 is provided within a portion of the compressed air passageway 688. The baffle 630 is movable within the compressed air passageway 688 via an arm 632.

The combustor 680 is similar to the combustor 80, 280, 380, 480, 580 in that it includes the compressed air passageway 688 at least partially defined within a radial space between the outer surface 606 and the casing 678. The difference, however, is that the compressed air passageway 688 includes a first channel 656 and a second channel 658 split by a wall 654 extending through the compressed air passageway 688. The wall 654 can start along any suitable axial location of the compressed air passageway 688 that is at least upstream of an axially forwardmost inlet 626 of the set of dilution passages 620. It is further contemplated that the wall 654 can join with the liner 682 downstream of the set of dilution passages 620 or that the first channel 656 and the second channel 658 can merge downstream of the set of dilution passages 620.

The inlet 626 can be fluidly coupled to the first channel 656 while the second channel 658 can be fluidly coupled to any suitable downstream portion of the gas turbine engine 10 (FIG. 1). A static arm 652 can operably couple to baffle 630 to the casing 678.

The baffle 630 is statically mounted to the static arm 652 and slidably coupled to the arm 632. As such, when the arm 632 is moved, the baffle 630 rotates about the static arm 652 to allow for the selective occlusion of the compressed air flow into the first channel 656.

As illustrated, the baffle 630 is in a first position where the first channel 656 and the second channel 658 are each open. As such, the compressed airflow (C) (FIG. 3) can flow into the first channel 656 and thus the inlet 626 as the second dilution airflow (D2) and into the second channel 658 as the bypass compressed airflow (Cb). The baffle 630 can at least partially occlude the compressed airflow (C) to the inlet 626. When partially occluding the first channel 656, the baffle 630 can act as a nozzle.

It is contemplated that the first channel 656 and the second channel 658 can be switched such that the first channel 656 is the second channel 658 and vice-versa. When the first channel 656 is provided radially outward from the second channel 658, with respect to the mean centerline 624, a dilution channel 668 (illustrated in phantom lines) can extend through the wall 654, the second channel 658 and to the dilution passage 620. In such a case, the dilution channel 668 is defined as a portion of the dilution passage 620 and the inlet 626 is provided on a portion of the wall 654 confronting the first channel 656. The dilution channel 668 can extend through a portion of the second channel 658. In such a configuration, the baffle 630 is used to occlude the compressed airflow (C) from the second channel 658 rather than the first channel 656.

FIG. 12 is a schematic side cross-sectional view of the baffle 630 of FIG. 11. As illustrated, the baffle 630 is in a second position where the first channel 656 and thus the inlet 626 is fully occluded from the compressed airflow (C) (FIG. 3). As such, the compressed airflow (C) flows entirely through the second channel 658 as the bypass compressed airflow (Cb).

FIG. 13 is a schematic side cross-sectional view of an exemplary baffle 730 provided within a combustor 780 suitable for use within the combustor 80 of FIG. 3. The combustor 780 is similar to the combustor 80, 280, 380, 480, 580, 680, therefore, like parts will be identified by like numerals increased to the 700 series with it being understood that the description of the combustor 80, 280, 380, 480, 580, 680 applies to the combustor 780 unless noted otherwise.

The combustor 780 includes a casing 778 and a liner 782 with an outer surface 706 and an inner surface 708. A dilution passage 720 extends through the liner 782 between an inlet 726 provided on the outer surface 706 and a dilution hole 722 provided on the inner surface 708. The inner surface 708 confronts and at least partially defines a combustion chamber 786. A mean centerline 724 extends through the combustion chamber 786. The outer surface 706 at least partially defines a compressed air passageway 788. The baffle 730 is provided within a portion of the compressed air passageway 788. The baffle 730 is movable within the compressed air passageway 788 via an arm 732.

The combustor 780 is similar to combustor 680 in that it includes the compressed air passageway 788 including a first channel 756 and a second channel 758 split by a wall 754 extending through the compressed air passageway 788. The difference, however, is that the baffle 730 is pivotable about a static arm 752 to fully uncover, partially cover, or fully cover both of the first channel 756 and the second channel 758. In other words, the baffle 730 is movable to fully cover or partially cover the first channel 756, leaving the second channel 758 fully uncovered and vice-versa. The baffle 730 allows for the selective fluid coupling of the compressed airflow (C) (FIG. 3) to one of or both of the first channel 756 and the second channel 758. The baffle 730 has a range of movement in both the radial direction and the axial direction.

FIG. 14 is a schematic side cross-sectional view an exemplary set of baffles 830 provided within a combustor 880 suitable for use within the combustor 80 of FIG. 3. The combustor 880 is similar to the combustor 80, 280, 380, 480, 580, 680, 780, therefore, like parts will be identified by like numerals increased to the 800 series with it being understood that the description of the combustor 80, 280, 380, 480, 580, 680, 780 applies to the combustor 880 unless noted otherwise.

The combustor 880 includes a casing 878, an outer liner 882a and an inner liner 882b each with an outer surface 806 and an inner surface 808. A dilution passage 820 extends through the outer and inner liners 882a, 882b between an inlet 826 provided on the outer surface 806 and a dilution hole 822 provided on the inner surface 808. The inner surface 808 confronts and at least partially defines a combustion chamber 886. A mean centerline 824 extends through the combustion chamber 886. The outer surface 806 at least partially defines a compressed air passageway 888. The set of baffles 830 are provided within respective portions of the compressed air passageway 888. Each baffle 830 of the set of baffles 830 is movable within the compressed air passageway 888 via an arm 832.

The combustor 880 is similar to the combustor 680, 780 in that the compressed air passageway 888 is split into a first channel 856 and a second channel 858 via a wall 854. The combustor 880 further includes at least two baffles 830; one baffle provided in a portion of the compressed air passageway 888 confronting the outer liner 882a and another baffle provided in a portion of the compressed air passageway 888 confronting the inner liner 882b. The first channel 856 can be provided radially outward from or radially inward from the second channel 858, with respect to the mean centerline 824.

The set of baffles 830 are operably coupled to a respective static arm 852. As illustrated, at least two baffles of the set of baffles 830 are operably coupled to a single static arm 852 and pivotable about the single static arm 852 via the movement of a single arm 832. The baffle 830 has a range of movement in both the radial direction and the axial direction. The static arm 852 can extend from opposing portions of a casing 878 or otherwise extend from one portion of the casing 878 and be directly coupled to a radially farthest baffle of the set of baffles 830. In either case, the static arm 852 can extend through or around the combustion chamber 886. Alternatively, the static arm 852 can be provided axially forward of the combustion chamber 886 and extend through a portion of the compressed air passageway 888.

As the at least two baffles of the set of baffles 830 are coupled to the same arm 832, the at least two baffles of the set of baffles 830 are dependently movable with respect to one another.

At least a portion of the combustor 880 can be non-symmetric about the mean centerline 824. As a non-limiting example, the first channel 856 and the second channel 858 radially nearest the outer liner 882a can be non-symmetric with respect to the first channel 856 and the second channel 858 provided radially nearest the inner liner 882b. In such a case, one of the first channel 856 would be radially outward from the second channel 858 such that a dilution channel 868 can be provided to interconnect the first channel 856 with a remainder of the dilution passage 820. Further, in such a case, the baffles 830 are non-symmetric about the mean centerline 824. Alternatively, the baffles 830, the first channel 856, and the second channel 858 can be symmetric about the mean centerline 824.

The benefit of utilizing the illustrated configuration where at least two baffles 830 are controlled by a single arm 832 is that the number of needed actuators (e.g., the actuator 136 of FIG. 3) is reduced. In other words, a single actuator can be used to move two or more baffles 830.

FIG. 15 is a schematic side cross-sectional view an exemplary set of baffles 930 provided within a combustor 980 suitable for use within the combustor 80 of FIG. 3. The combustor 980 is similar to the combustor 80, 280, 380, 480, 580, 680, 780, 880, therefore, like parts will be identified by like numerals increased to the 900 series with it being understood that the description of the combustor 80, 280, 380, 480, 580, 680, 780, 880 applies to the combustor 980 unless noted otherwise.

The combustor 980 includes a casing 978 an outer liner 982a and an inner liner 982b each with an outer surface 906 and an inner surface 908. A dilution passage 920 extends through the outer and inner liners 982a, 982b between an inlet 926 provided on the outer surface 906 and a dilution hole 922 provided on the inner surface 908. The inner surface 908 confronts and at least partially defines a combustion chamber 986. A mean centerline 924 extends through the combustion chamber 986. The outer surface 906 at least partially defines a compressed air passageway 988. The set of baffles 930 are provided within respective portions of the compressed air passageway 988. Each baffle 930 of the set of baffles 930 is movable within the compressed air passageway 988 via an arm 932.

The combustor 980 is similar to the combustor 680, 780, 880 in that the compressed air passageway 988 is split into a first channel 956 and a second channel 958 via a wall 954. The combustor 980 is similar to the combustor 880 in that it includes a single static arm 952 operably coupling two or more baffles 930 to the casing 978. The combustor 980, however, includes two independently movable baffles 930 coupled to the same static arm 952. In other words, each baffle 930 includes a respective arm 932 coupled to a respective actuator (not illustrated, e.g., actuator 136 of FIG. 3). Further, the set of baffles 930, the arms 932, the static arm 952, the first channel 956 and the second channel 958 can by symmetric about the mean centerline 924.

FIG. 16 is a schematic side cross-sectional view an exemplary set of baffles 1030 provided within a combustor 1080 suitable for use within the combustor 80 of FIG. 3. The combustor 1080 is similar to the combustor 80, 280, 380, 480, 580, 680, 780, 880, 980, therefore, like parts will be identified by like numerals increased to the 1000 series with it being understood that the description of the combustor 80, 280, 380, 480, 580, 680, 780, 880, 980 applies to the combustor 1080 unless noted otherwise.

The combustor 1080 includes a casing 1078, an outer liner 1082a and an inner liner 1082b. The combustor 1080 is defined by a combustor centerline 1070. A dilution passage 1020 extends through the outer and inner liners 1082a, 1082b between an inlet 1026 and a dilution hole 1022. The inner liner 1082b and the outer liner 1082a at least partially define a combustion chamber 1086. A mean centerline 1024 extends through the combustion chamber 1086. A compressed air passageway 1088 extends around the inner liner 1082b and the outer liner 1082a. The set of baffles 1030 are provided within respective portions of the compressed air passageway 1088. Each baffle 1030 of the set of baffles 1030 is movable within the compressed air passageway 1088 via an arm 1032 coupled to an actuator 1036.

The combustor 1080 is similar to the combustor 80, 280, 380, 480, 580, 680, 780, 880, 980 in that it includes a fuel cup 1076 that exhausts a flame or fuel/air mixture into the combustion chamber 1086. The combustor 1080, however, includes the mean centerline 1024 that turns upwardly (e.g. . . . , radially) away from the combustor centerline 1070.

Each baffle of the set of baffles 1030 can be radially or axially moveable with respect to the mean centerline 1024. It will be appreciated that the set of baffles 1030 can be provide along a portion of the combustor 1080 where the mean centerline 1024 is non-parallel to the combustor centerline 1070. When radially movable with respect to the mean centerline 1024, each radially movable baffle of the set of baffles 1030 is axially movable with respect to the combustor centerline 1070. When axially movable with respect to the mean centerline 1024, each axially movable baffle of the set of baffles 1030 is radially movable with respect to the combustor centerline 1070.

It will be appreciated that the set of baffles 130, 230, 330, 430, 530, 630, 730, 830, 930, 1030 can be applied to any suitable combustor.

FIG. 17 is a schematic transverse cross-sectional view of an exemplary combustor 1180 suitable for use as the combustor 80 of FIG. 3. The combustor 1180 is similar to the combustor 80, 280, 380, 480, 580, 680, 780, 880, 980, therefore, like parts will be identified by like numerals increased to the 1100 series with it being understood that the description of the combustor 80, 280, 380, 480, 580, 680, 780, 880, 980 applies to the combustor 1180 unless noted otherwise.

The combustor 1180 includes a casing 1178, an outer liner 1182a and an inner liner 1182b. The combustor 1180 is defined by a combustor centerline 1170. A dilution passage 1120 extends through the outer and inner liners 1182a between an inlet 1126 and a dilution hole 1122. The inner liner 1182b and the outer liner 1182a at least partially define a combustion chamber 1186. A mean centerline 1124 extends through the combustion chamber 1186. A compressed air passageway 1188 extends around the inner liner 1182b and the outer liner 1182a. A set of fuel cups 1176 exhaust into the combustion chamber 1186.

A set of baffles 1130 are provided within the compressed air passageway 1188 to occlude a flow of compressed air (C) (FIG. 3) from a respective portion of the set of dilution passages 1120. The set of baffles 1130 include at least two circumferentially opposing baffles that are coupled to a single arm 1132 at circumferentially opposing ends of the single arm 1132. The opposing baffles of the set of baffles 1130 can be provided at a first radial height (Rh1) and a second radial height (Rh2), respectively, from the mean centerline 1124. The first radial height (Rh1) can be smaller than the second radial height (Rh2) such that when a portion of the dilution passages of the set of dilution passages are fully covered by the baffle at the first radial height (Rh1), another portion of the dilution passages of the set of dilution passages 1120 are partially covered or fully uncovered by the baffle at the second radial height (Rh2). Alternatively, the first radial height (Rh1) and the second radial height (Rh2) can be equal. The set of baffles 1130 have a range of movement that has a degree of freedom in at least one of the radial direction or an axial direction.

Benefits of the present disclosure include a combustor suitable for use with a hydrogen-containing fuel. As outlined previously, hydrogen-containing fuels have a higher flame temperature and velocity than traditional fuels (e.g., fuels not containing hydrogen). That is, hydrogen or a hydrogen mixed fuel typically has a wider flammable range and a faster burning velocity than traditional fuels such petroleum-based fuels, or petroleum and synthetic fuel blends. These high burn temperatures of hydrogen-containing fuel mean that additional insulation is needed between the ignited hydrogen-containing fuel and surrounding components of the gas turbine engine (e.g., the inner/outer liner, and other parts of the gas turbine engine). The combustor, as described herein, includes the baffle that can fully or at least partially occlude the second dilution airflow to the combustion chamber. This, in turn, is used for flame shaping purposes, as described herein. As a non-limiting example, the control of the second dilution airflow can direct the flame away from the liner, thus ensuring the liner is not overly heated. Further, the baffle is used to create a uniform flame temperature within the combustion chamber. The shaping can further ensure that the combustion section or otherwise hot sections of the turbine engine do not fail or otherwise become ineffective by being overly heated, thus increasing the lifespan of the turbine engine.

Benefits associated with using hydrogen-containing fuel over conventional fuels include an eco-friendlier engine as the hydrogen-containing fuel, when combusted, generates less carbon pollutants than a combustor using conventional fuels. For example, a combustor including 100% hydrogen-containing fuel (e.g., the fuel is 100% H₂) would have zero carbon pollutants. The combustor, as described herein, can be used in instances where 100% hydrogen-containing fuel is used.

Further benefits associated with using hydrogen-containing fuel over conventional fuels include a gas turbine engine that can utilize less fuel due to higher heating value of fuel to achieve same turbine inlet temperatures. For example, a conventional gas turbine engine using conventional fuels will require more fuel to produce the same amount of work or engine output as the present gas turbine engine using hydrogen-containing fuels. This, in turn, means that either less amount of fuel can be used to generate the same amount of engine output as a conventional gas turbine engine, or the same amount of fuel can be used to generate an increased engine output when compared to the conventional gas turbine engine.

To the extent not already described, the different features and structures of the various embodiments can be used in combination, or in substitution with each other as desired. That one feature is not illustrated in all of the embodiments is not meant to be construed that it cannot be so illustrated, but is done for brevity of description. Thus, the various features of the different embodiments can be mixed and matched as desired to form new embodiments, whether or not the new embodiments are expressly described. All combinations or permutations of features described herein are covered by this disclosure.

This written description uses examples to describe aspects of the disclosure described herein, including the best mode, and also to enable any person skilled in the art to practice aspects of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of aspects of the disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

Further aspects are provided by the subject matter of the following clauses:

A combustor for a gas turbine engine, the combustor comprising a casing, an inner liner and an outer liner, a compressed air passageway formed between the casing, the inner liner and the outer liner, a combustion chamber at least partially defined by the inner liner and the outer liner, the combustion chamber having a mean centerline extending through the combustion chamber, the mean centerline being equidistant between the inner liner and the outer liner, at least one dilution passage extending through at least one of the inner liner and the outer liner, the at least one dilution passage extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber, and a baffle provided within the compressed air passageway, the baffle having a range of movement between a first position and a second position relative to the inlet of the at least one dilution passage to control a degree of occlusion of compressed airflow to the inlet.

A combustor for a gas turbine engine, the combustor comprising a casing, an inner liner and an outer liner, a compressed air passageway formed between the casing, the inner liner and the outer liner, with at least a portion of the compressed air passageway being split, via a wall, between a first channel and a second channel, a combustion chamber at least partially defined by the inner liner and the outer liner, the combustion chamber having a mean centerline extending through the combustion chamber, the mean centerline being equidistant between the inner liner and the outer liner, at least one dilution passage fluidly extending through at least one of the inner liner and the outer liner, the at least one dilution passage extending between an inlet directly fluidly coupled to the first channel and a dilution hole directly fluidly coupled to the combustion chamber, and a first arm, a second arm statically coupled to a portion of the casing, and a first baffle extending between the first arm and the second arm, the first baffle provided within the compressed air passageway and having a range of movement between a first position and a second position relative to the inlet of the at least one dilution passage to control a degree of occlusion of compressed airflow to the first channel.

A method of fluidly coupling a flow of compressed air to a combustion chamber of a combustor, the method comprising selectively occluding the flow of compressed air to at least one dilution passage through selective movement of a baffle along a degree of freedom.

The combustor of any preceding clause, wherein the range of movement has a degree of freedom in at least one of a radial direction or an axial direction, with respect to the mean centerline.

The combustor of any preceding clause, wherein the degree of freedom is in the radial direction and the baffle confronts the casing in the second position.

The combustor of any preceding clause, wherein the degree of freedom is in the axial direction.

The combustor of any preceding clause, wherein the at least one dilution passage includes at least one axially downstream dilution passage that is axially downstream an axially upstream dilution passage, with the baffle being movable such that the axially downstream dilution passage and the axially upstream dilution passage have varying degrees of occlusion.

The combustor of any preceding clause, wherein the at least one dilution passage is included within a plurality of dilution passages, with the baffle extending across and occluding the compressed airflow to the plurality of dilution passages.

The combustor of any preceding clause, wherein the baffle includes a major body axis oriented at a radial baffle angle with respect to the mean centerline.

The combustor of any preceding clause, wherein the radial baffle angle is wherein the radial baffle angle is non-zero.

The combustor of any preceding clause, wherein the baffle includes a circumferential baffle angle when viewed along a circumferential plane intersecting the baffle, with the circumferential baffle angle has an absolute value of less than 90 degrees.

The combustor of any preceding clause, wherein the baffle is operably coupled to an arm.

The combustor of any preceding clause, wherein the baffle includes a pair of opposing baffles and wherein the pair of opposing baffles extend from opposing circumferential sides of the arm.

The combustor of any preceding clause, wherein the pair of opposing baffles are provided at varying radial heights from the mean centerline.

The combustor of any preceding clause, further comprising, a first fuel cup extending through a dome wall at least partially defining the combustion chamber, and a second fuel cup extending through the dome wall and being circumferentially spaced from the first fuel cup, with respect to the mean centerline, wherein a first baffle of the pair of opposing baffles extends circumferentially across the first fuel cup and a second baffle of the pair of opposing baffles extends circumferentially across the second fuel cup.

The combustor of any preceding clause, wherein the at least one dilution passage is included within a plurality of dilution passages provided on both the inner liner and the outer liner, with the dilution passages of the plurality of dilution passages provided on the inner liner and the dilution passages of the plurality of dilution passages provided on the outer liner being occluded by separate baffles.

The combustor of any preceding clause, wherein the combustor is defined by a combustor centerline and the baffle is movable at least one of either axially or radially, with respect to the combustor centerline.

The combustor of any preceding clause, wherein the combustor centerline is non-parallel to the mean centerline at the inlet.

The combustor of any preceding clause, further comprising at least one fuel cup provided on a dome wall at least partially defining the combustion chamber, the at least one fuel cup receiving a flow of hydrogen containing fuel.

The combustor of any preceding clause, wherein the first baffle is located within a portion of the compressed air passageway radially outward from the outer liner.

The combustor of any preceding clause, further comprising a second baffle located within a portion of the compressed air passageway radially inward from the inner liner, the second baffle being pivotable about the second arm, via the first arm.

The combustor of any preceding clause, wherein the baffle sits flush against an outer surface of one of the outer liner or the inner liner when viewed along a radial plane extending perpendicularly from the mean centerline and intersecting the baffle.

The combustor of any preceding clause, wherein the at least one dilution passage is included within a plurality of dilution passages, each having a respective dilution passage centerline.

The combustor of any preceding clause, wherein the dilution passage centerline intersects the inlet of a respective dilution passage at a center point.

The combustor of any preceding clause, wherein a line extends through each center point of the plurality of dilution passages.

The combustor of any preceding clause, wherein the baffle includes a major body axis.

The combustor of any preceding clause, wherein the major body axis is parallel to the line.

The combustor of any preceding clause, wherein the major body axis is non-parallel to the line.

The combustor of any preceding clause, wherein the inlet is 100% occluded when the baffle is in the first position and 0% occluded when in the second position.

The method of any preceding clause, further comprising fully occluding the compressed airflow to the at least one dilution passage during a relight condition of the combustor.

COMBUSTOR WITH A DILUTION PASSAGE

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