The present subject matter relates generally to gas turbine engine combustion assemblies for gas turbine engines.
Combustion assemblies for gas turbine engines generally include orifices in the combustion liners to dilute the combustion gases within the combustion chamber with air from the diffuser cavity. The air may be employed to mix with an over rich combustion gas mixture to complete the combustion process; to stabilize combustion flames within the recirculation zone of the combustion chamber; to minimize oxides of nitrogen emissions; or to decrease combustion gas temperature before egressing to the turbine section.
Although dilution orifices provide known benefits, there is a need for structures that may provide and improve upon these benefits via egressing the air into the combustion chamber in increasingly detailed or specific modes.
Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.
The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening. The liner includes a walled chute disposed at least partially within the opening. The walled chute defines an inner surface at least partially defining a jet destabilizer.
In various embodiments, the walled chute includes a span of the inner surface from a cold end proximate to the pressure plenum to a hot end proximate to the combustion chamber. The jet destabilizer includes a contoured surface is defined within approximately 33% of the span from the hot end. In one embodiment, the contoured surface defines a chevron, a waveform, a rib structure, or a vane structure.
In still various embodiments, the inner surface at least partially defines a groove. In one embodiment, the groove is defined substantially helical. In another embodiment, the groove is defined substantially perpendicular to the inner surface.
In still yet various embodiments, the jet destabilizer defines a member extended from the inner surface at least partially across the opening. In one embodiment, the member is extended from the inner surface of the walled chute substantially perpendicular to a direction of flow of combustion gases formed within the combustion chamber. In another embodiment, the member is extended from the inner surface of the walled chute substantially co-directional to a direction of flow of combustion gases formed within the combustion chamber.
In one embodiment, the walled chute is extended at least partially into the combustion chamber.
Another aspect of the present disclosure is directed to a gas turbine engine including a combustor assembly. The combustor assembly includes a liner defining a combustion chamber therebetween and a pressure plenum surrounding the liner. The liner defines an opening. The liner includes a walled chute disposed at least partially within the opening. The walled chute includes an inner surface. The inner surface includes a jet destabilizer in a first flow passage defined within the walled chute.
In various embodiments, the jet destabilizer includes a member extended across a diameter of the opening of the liner. In one embodiment, the member is extended from the inner surface substantially perpendicular to a direction of flow of combustion gases formed within the combustion chamber. In another embodiment, the member is extended from the inner surface substantially co-directional to a direction of flow of combustion gases formed within the combustion chamber.
In still various embodiments, the jet destabilizer is defined at the inner surface between a cold end and a hot end of the first flow passage. In one embodiment, the jet destabilizer is defined within 33% of the walled chute from the cold end or the hot end.
In one embodiment, the walled chute comprises equal to or less than six times a diameter of the opening of the liner.
In another embodiment, the jet destabilizer comprises a groove defined at the inner surface of the walled chute.
In still another embodiment, the jet destabilizer comprises a chevron, a waveform, a rib structure, or a vane structure at the walled chute.
These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
A full and enabling disclosure of the present invention, 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:
Repeat use of reference characters in the present specification and drawings is intended to represent the same or analogous features or elements of the present invention.
Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.
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 “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows.
Embodiments of combustor assembly dilution structures are generally provided that may improve emissions and combustion gas quenching via egressing the air into the combustion chamber in increasingly detailed or specific modes. The various embodiments of combustor assemblies generally define a walled chute configured to egress air from the diffuser cavity to the combustion chamber in multiple or tailored modes.
Referring now to the drawings,
The core engine 16 may generally include a substantially tubular outer casing 18 that defines an annular inlet 20. The outer casing 18 encases or at least partially forms, in serial flow relationship, a compressor section having a booster or low pressure (LP) compressor 22, a high pressure (HP) compressor 24, a combustion section 26, a turbine section including a high pressure (HP) turbine 28, a low pressure (LP) turbine 30 and a jet exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In particular embodiments, as shown in
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Referring still to
During operation of the engine 10, as shown in
The compressed air 82 pressurizes the pressure plenum 84. A first portion of the of the compressed air 82, as indicated schematically by arrows 82(a) flows from the pressure plenum 84 into the combustion chamber 62 where it is mixed with the fuel 72 and burned, thus generating combustion gases, as indicated schematically by arrows 86, within the combustor 50. Typically, the LP and HP compressors 22, 24 provide more compressed air to the pressure plenum 84 than is needed for combustion. Therefore, a second portion of the compressed air 82 as indicated schematically by arrows 82(b) may be used for various purposes other than combustion. For example, as shown in
Additionally, at least a portion of compressed air 82(b) flows out of the pressure plenum 84 into the combustion chamber 62 via the first flow passage 111 defined by the walled chute 100, such as depicted via arrows 83. A portion of the compressed air 82(b), shown as air 83, egresses from the pressure plenum 84 through the first flow passage 111 into the combustion chamber 62.
Referring now to
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In another embodiment, such as generally provided in regard to
In yet another embodiment, such as generally provided in regard to
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In one embodiment, such as generally provided in regard to
It should be appreciated that various embodiments of the contoured surface 103 may defining the chevrons or waveforms 113 may define a triangle waveform, square or rectangular or step waveform, a sinusoidal waveform, a sawtooth waveform, or other waveform. Additionally, or alternatively, the chevron or waveforms 113 may be defined regular (e.g., constant frequency) along the walled chute 100. In other embodiments, the chevron or waveforms 113 may be defined irregularly (e.g., variable, asymmetric, or irregular frequency) along the walled chute 100.
Embodiments of the contoured surface 103 may generally enable, promote, or increase turbulence in the flow of air 83 from the pressure plenum 84 to the combustion chamber 62. The increased turbulence of the flow of air 83 may improve mixing of the flow of air 83 with the combustion gases 86 such as to decrease production of nitrogen oxides (e.g., NOx), improve durability of the combustor assembly 50 (e.g., improve durability at the liners 52, 54), or both. As another example, the walled chute 100 including the contoured surface 103 may further improve mixing of the flow of air 83 with the combustion gases 86 while mitigating losses in penetration of the flow of air 83 with the combustion gases 86 into the combustion chamber 62.
Referring to
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In one embodiment, such as generally provided in regard to
In other embodiments, such as generally provided in regard to
In another embodiment of the walled chute 100, such as generally provided in regard to
Referring now to
Various embodiments of the engine 10 and combustor assembly 50 may define a rich burn combustor in which the walled chute 100 may define dilution jets providing additional mixing air (e.g., air 83) with a mixture of combustion gases (e.g., combustion gases 86) to improve or complete the combustion process. The walled chute 100 may further define dilution jets that further enable or augment a combustion recirculation zone within the combustion chamber 62 to stabilize a flame therein. Still further, the walled chute 100 may define dilution jets that may relatively rapidly quench the combustion gases 86 to minimize production of nitrogen oxides. Furthermore, various embodiments of the combustor assembly 50 and walled chute 100 shown and described herein may enable customization of a distribution of combustion gas temperature to improve durability of components at or downstream of the combustor assembly 50 (e.g., the liners 52, 54, the HP turbine 28).
Still further, the walled chute 100 may generally define the member 110 as a bluff-body device such as to provide a jet destabilizer to modify counter rotating vortex pairs (CVP) formed in jets in cross flow (JIC). For example, the portion of air 83 provided through the walled chute 100 may define a CVP formed relative to the flow of combustion gases 86 defining a JIC.
All or part of the combustor assembly may be part of a single, unitary component and may be manufactured from any number of processes commonly known by one skilled in the art. These manufacturing processes include, but are not limited to, those referred to as “additive manufacturing” or “3D printing”. Additionally, any number of casting, machining, welding, brazing, or sintering processes, or any combination thereof may be utilized to construct the combustor 50, including, but not limited to, the liners 52, 54, the walled chute 100, the member 110, or combinations thereof. Furthermore, the combustor assembly may constitute one or more individual components that are mechanically joined (e.g. by use of bolts, nuts, rivets, or screws, or welding or brazing processes, or combinations thereof) or are positioned in space to achieve a substantially similar geometric, aerodynamic, or thermodynamic results as if manufactured or assembled as one or more components. Non-limiting examples of suitable materials include high-strength steels, nickel and cobalt-based alloys, and/or metal or ceramic matrix composites, or combinations thereof.
Various embodiments of the walled chute 100 including the member 110 may define the member 110 of one or more cross sectional areas, such as, but not limited to, a circular cross section (e.g., shown in
Additionally, or alternatively, various embodiments of the walled chute 100 and/or the opening 105 through which the walled chute 100 is disposed may define one or more cross sectional areas, such as, but not limited to, a circular cross section (e.g., shown in
This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention 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 include 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.