The present subject matter relates generally to wall assemblies for heat engines. The present subject matter relates more specifically to wall assemblies for hot sections of heat engines.
Combustor assemblies for heat engines such as turbo machines include liners and wall assemblies to define combustion chambers at which fuel and oxidizer are mixed and ignited to produce combustion gases that flow downstream to generate thrust. Combustor assemblies must generally control flows of oxidizer entering, egressing, or flowing around the combustion chamber such as to improve combustion efficiency and performance. As such, there is a need for wall assemblies and sealing devices for combustor assemblies to improve leakage control or flow variation such as to improve combustion efficiency and performance.
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.
An aspect of the present disclosure is directed to a combustor assembly for a heat engine. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly including a radially extended first wall disposed adjacent to the combustion chamber. The deflector assembly further includes an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.
In various embodiments, the second wall and the first wall together define a cavity therebetween. In one embodiment, a seal is disposed in the cavity. In another embodiment, the seal is extended 360 degrees through the cavity defining an annulus through the deflector assembly. In yet another embodiment, the second wall includes a radially extended portion adjacent to the first wall. The first wall and the radially extended portion of the second wall together define the cavity. In still yet another embodiment, the first wall includes a portion extended at an acute radial angle. The second wall and the portion of the first wall together define the cavity. In another embodiment, the second wall includes a pair of axially extended portions separated radially by a radially extended portion. The cavity is defined between the first wall and the pair of axially extended portions and the radially extended portion of the second wall.
In one embodiment, the deflector assembly defines an adjustable radial gap between the first wall and the liner wall.
In another embodiment, the second wall and the first wall together define a labyrinth seal assembly.
In still another embodiment, the first wall and the liner wall together define a labyrinth seal assembly.
In various embodiments, the second wall is coupled to the first wall. In one embodiment, the second wall and the first wall are coupled together at an interface. The interface defines an approximately 45 degree joint at the first wall and the second wall. In one embodiment, the second wall defines an opening therethrough in fluid communication with a combustion chamber.
Another aspect of the present disclosure is directed to a heat engine. The heat engine includes a combustion section including a combustor assembly. The combustor assembly includes an inner liner and an outer liner radially spaced apart and defining a combustion chamber therebetween. The combustor assembly further includes a deflector assembly disposed at an upstream end of the liners. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liners.
In various embodiments, the second wall and the first wall together define a cavity therebetween.
In one embodiment, the cavity defines a substantially serpentine passage.
In another embodiment, the second wall includes a pair of axially extended portions separated radially by a radially extended portion. The cavity is defined between the first wall and the pair of axially extended portions and the radially extended portion of the second wall.
In still another embodiment, the first wall includes a portion extended at an acute radial angle between 15 degrees and 75 degrees relative to a fuel nozzle centerline. The second wall and the portion of the first wall together define the cavity.
In still various embodiments, a seal is disposed in the cavity. In one embodiment, the seal is extended 360 degrees through the cavity defining an annulus through the deflector assembly.
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.
Approximations recited herein may include margins based on one more measurement devices as used in the art, such as, but not limited to, a percentage of a full scale measurement range of a measurement device or sensor. Alternatively, approximations recited herein may include margins of 10% of an upper limit value greater than the upper limit value or 10% of a lower limit value less than the lower limit value.
Embodiments of a heat engine and a combustor assembly are generally provided that may improve leakage control. The various embodiments described herein may limit leakage or flow variation across a deflector assembly into the combustion chamber. Such limitation of leakage or flow variation may improve combustion efficiency, reduce issues regarding combustion emissions or dynamics due to excessive leakage, and generally improve engine efficiency.
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
As shown in
It should be appreciated that although the exemplary embodiment of the combustor assembly 50 of
As shown in
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
Referring to
Referring still to
Referring now to
In various embodiments, the second wall 120 is selectively coupled to the first wall 110. During operation of the engine 10, the second wall 120 and/or the first wall 110 may expand or contract from contact with one another based on an operating condition of the engine 10 (e.g., a pressure, temperature, or flow rate of air through the engine 10). An interface 118 at which the second wall 120 and the first wall 110 contact may generally be defined at an aft end of the second wall 120 (e.g., toward aft end 98). The interface 118 is further generally defined at a radially outward end of the first wall 110. The interface 118 may further include the first wall 110 and the second wall 120 proximate or close to the liner wall 130. In one embodiment, such as generally depicted in
During operation of the engine 10, the interface 118 may expand or contract such as to separate and contact together the first wall 110 and the second wall 120 from the interface 118. For example, the second wall 120 may expand toward the first wall 110 at the interface 118 as the operating condition changes, such as the temperature and/or pressure of the flow of fluid 82 (
Referring now to
The cavity 115 and seal 140 may together substantially control or prevent a flow of fluid through the cavity 115 to the combustion chamber 62, such as to improve leakage control and improve combustion performance.
Referring still to
In various embodiments the second wall 120 includes a radially extended portion 122. Referring to
In still various embodiments, the first wall 110 includes a portion 112 extended at least partially along the axial direction A. In one embodiment, such as depicted in regard to
Referring now to
Referring to
Referring now to
Referring to
Referring still to
In still various embodiments, such as generally depicted in
Referring now to
Referring now to
All or part of the combustor assembly 50 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 first wall 110, the second wall 120, the liner 130, the seal 140, 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.
Embodiments of the engine 10 and combustor assembly 50 generally shown and described herein may improve leakage control. The various embodiments described herein may limit leakage or flow variation across the deflector assembly 100 into the combustion chamber 62. Such limitation of leakage or flow variation may improve combustion efficiency, reduce issues regarding combustion emissions or dynamics due to excessive leakage, and generally improve engine efficiency.
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.
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