Flow control wall for heat engine

A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.

FIELD

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.

BACKGROUND

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.

BRIEF DESCRIPTION

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.

DETAILED DESCRIPTION

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,FIG. 1is a schematic partially cross-sectioned side view of an exemplary high bypass turbofan engine10herein referred to as “engine10” as may incorporate various embodiments of the present disclosure. Although further described below with reference to a turbofan engine, the present disclosure is also applicable to turbomachinery in general, including turbojet, turboprop, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. As shown inFIG. 1, the engine10has a longitudinal or axial engine centerline axis12that extends there through for reference purposes. The engine10defines a longitudinal direction L and an upstream end99and a downstream end98along the longitudinal direction L. The upstream end99generally corresponds to an end of the engine10along the longitudinal direction L from which air enters the engine10and the downstream end98generally corresponds to an end at which air exits the engine10, generally opposite of the upstream end99along the longitudinal direction L. In general, the engine10may include a fan assembly14and a core engine16disposed downstream from the fan assembly14.

The core engine16may generally include a substantially tubular outer casing18that defines an annular inlet20. The outer casing18encases or at least partially forms, in serial flow relationship, a compressor section having a booster or low pressure (LP) compressor22, a high pressure (HP) compressor24, a combustion section26, a turbine section including a high pressure (HP) turbine28, a low pressure (LP) turbine30and a jet exhaust nozzle section32. A high pressure (HP) rotor shaft34drivingly connects the HP turbine28to the HP compressor24. A low pressure (LP) rotor shaft36drivingly connects the LP turbine30to the LP compressor22. The LP rotor shaft36may also be connected to a fan shaft38of the fan assembly14. In particular embodiments, as shown inFIG. 1, the LP rotor shaft36may be connected to the fan shaft38by way of a reduction gear40such as in an indirect-drive or geared-drive configuration. In other embodiments, the engine10may further include an intermediate pressure compressor and turbine rotatable with an intermediate pressure shaft altogether defining a three-spool gas turbine engine.

As shown inFIG. 1, the fan assembly14includes a plurality of fan blades42that are coupled to and that extend radially outwardly from the fan shaft38. An annular fan casing or nacelle44circumferentially surrounds the fan assembly14and/or at least a portion of the core engine16. In one embodiment, the nacelle44may be supported relative to the core engine16by a plurality of circumferentially-spaced outlet guide vanes or struts46. Moreover, at least a portion of the nacelle44may extend over an outer portion of the core engine16so as to define a bypass airflow passage48therebetween.

FIG. 2is a cross sectional side view of an exemplary combustion section26of the core engine16as shown inFIG. 1. As shown inFIG. 2, the combustion section26may generally include an annular type combustor50having an annular inner liner52, an annular outer liner54and a bulkhead56that extends radially between upstream ends of the inner liner52and the outer liner54respectively. In other embodiments of the combustion section26, the combustion assembly50may be a can-annular type. The combustor50further includes a deflector assembly100extended radially between the inner liner52and the outer liner54downstream of the bulkhead56. As shown inFIG. 2, the inner liner52is radially spaced from the outer liner54with respect to engine centerline12(FIG. 1) and defines a generally annular combustion chamber62therebetween. In particular embodiments, the inner liner52, the outer liner54, and/or the deflector assembly100may be at least partially or entirely formed from metal alloys or ceramic matrix composite (CMC) materials.

It should be appreciated that although the exemplary embodiment of the combustor assembly50ofFIG. 2depicts an annular combustor, various embodiments of the engine10and combustion section26may define a can-annular or can combustor configuration.

As shown inFIG. 2, the inner liner52and the outer liner54may be encased within an outer casing64. An outer flow passage66of a diffuser cavity or pressure plenum84may be defined around the inner liner52and/or the outer liner54. The inner liner52and the outer liner54may extend from the bulkhead56towards a turbine nozzle or inlet to the HP turbine28(FIG. 1), thus at least partially defining a hot gas path between the combustor assembly50and the HP turbine28. A fuel nozzle70may extend at least partially through the bulkhead56to provide a fuel72to mix with the air82(a) and burn at the combustion chamber62. In various embodiments, the bulkhead56includes a fuel-air mixing structure attached thereto (e.g., a swirler assembly).

During operation of the engine10, as shown inFIGS. 1 and 2collectively, a volume of air as indicated schematically by arrows74enters the engine10through an associated inlet76of the nacelle44and/or fan assembly14. As the air74passes across the fan blades42a portion of the air as indicated schematically by arrows78is directed or routed into the bypass airflow passage48while another portion of the air as indicated schematically by arrow80is directed or routed into the LP compressor22. Air80is progressively compressed as it flows through the LP and HP compressors22,24towards the combustion section26. As shown inFIG. 2, the now compressed air as indicated schematically by arrows82flows into a diffuser cavity or pressure plenum84of the combustion section26. The pressure plenum84generally surrounds the inner liner52and the outer liner54, and generally upstream of the combustion chamber62.

The compressed air82pressurizes the pressure plenum84. A first portion of the of the compressed air82, as indicated schematically by arrows82(a) flows from the pressure plenum84into the combustion chamber62where it is mixed with the fuel72and burned, thus generating combustion gases, as indicated schematically by arrows86, within the combustor50. Typically, the LP and HP compressors22,24provide more compressed air to the pressure plenum84than is needed for combustion. Therefore, a second portion of the compressed air82as indicated schematically by arrows82(b) may be used for various purposes other than combustion. For example, as shown inFIG. 2, compressed air82(b) may be routed into the outer flow passage66to provide cooling to the inner and outer liners52,54.

Referring toFIG. 3, a cross sectional view of an exemplary embodiment of a portion of the combustor assembly50is generally provided. A fuel nozzle centerline13is extended substantially along the longitudinal direction L. The combustor assembly50includes a first wall110extended along a radial direction R and a second wall120extended substantially along an axial direction A. In various embodiments, the first wall110defines the radially extended wall or deflector wall57(FIG. 3) of the deflector assembly100adjacent to the combustion chamber62. In one embodiment, the second wall120defines an axially extended wall of the dome assembly56. In another embodiment, a liner wall130defining the combustion chamber62radially therewithin is the inner liner52, the outer liner54, or both. It should be appreciated that in various embodiments the liner wall130may define a liner of a combustor can. For example, the liner wall may extend circumferentially substantially cylindrically around the deflector assembly100.

Referring still toFIG. 3, the liner wall130and the second wall120are coupled together. As depicted in regard toFIG. 3, the liner wall130and the second wall120may be coupled in radially adjacent or stacked arrangement. The liner wall130and the second wall120may be coupled together via one or more fastening or bonding methods or processes. For example, such as depicted in regard toFIG. 3, the liner wall130and the second wall120may be coupled together via a mechanical fastener150extended through each wall120,130. The mechanical fastener150may define combinations of bolt and nut, screw, tie rod, etc. However, in other embodiments, the walls120,130may be coupled together via a bonding process, such as, but not limited to, welding, brazing, adhesive, etc. In still various embodiments, the liner wall130and the second wall120are attached or coupled directly together.

Referring now toFIGS. 4-11, exemplary schematic embodiments of a portion of the combustor assembly50ofFIG. 3are generally provided. In various embodiments, the second wall120is disposed forward (e.g., toward the forward end99) of the first wall110and adjacent to the first wall110.

In various embodiments, the second wall120is selectively coupled to the first wall110. During operation of the engine10, the second wall120and/or the first wall110may expand or contract from contact with one another based on an operating condition of the engine10(e.g., a pressure, temperature, or flow rate of air through the engine10). An interface118at which the second wall120and the first wall110contact may generally be defined at an aft end of the second wall120(e.g., toward aft end98). The interface118is further generally defined at a radially outward end of the first wall110. The interface118may further include the first wall110and the second wall120proximate or close to the liner wall130. In one embodiment, such as generally depicted inFIG. 4, the interface118defines an approximately 45 degree joint at the first wall110and the second wall120.

During operation of the engine10, the interface118may expand or contract such as to separate and contact together the first wall110and the second wall120from the interface118. For example, the second wall120may expand toward the first wall110at the interface118as the operating condition changes, such as the temperature and/or pressure of the flow of fluid82(FIG. 1) increasing (e.g., with increased rotational speed of the HP shaft34and/or LP shaft36). As another example, the second wall120may contract from the first wall110from the interface118as the operating condition changes, such as the temperature and/or pressure of the flow of fluid82(FIG. 1) decreasing corresponding to a decrease in rotational speed at the engine10.

Referring now toFIGS. 5-7, additional exemplary embodiments of the portion of the combustor assembly50are generally provided. In various embodiments, the second wall120and the first wall110may together define a cavity115therebetween. In still various embodiments, a seal140may be disposed in the cavity115. In one embodiment, the seal140is extended substantially 360 degrees through the cavity115. In other embodiments, the seal140may include a plurality of seals or pieces thereof connected to extend substantially 360 degrees through the cavity115. For example, the cavity115may define an annulus through the deflector assembly100, such as relative to the combustor centerline13.

The cavity115and seal140may together substantially control or prevent a flow of fluid through the cavity115to the combustion chamber62, such as to improve leakage control and improve combustion performance.

Referring still toFIGS. 4-11, the deflector assembly100may generally define an adjustable radial gap125by which the first wall110may generally be separated from the liner wall130. The radial gap125may be substantially controlled by the flow of fluid permitted therethrough via the cavity115based on changes in the operating condition such as described above.

In various embodiments the second wall120includes a radially extended portion122. Referring toFIGS. 5-6, in various embodiments, the second wall120may further include a pair of axially extended portions121separated radially by the radially extended portion122. The cavity115may generally be defined between the first wall110and the pair of axially extended portions121and the radially extended portion122of the second wall120.

In still various embodiments, the first wall110includes a portion112extended at least partially along the axial direction A. In one embodiment, such as depicted in regard toFIGS. 5-7, the portion112is extended substantially along the axial direction A and further defines the cavity115with the second wall120. In still various embodiments, the portion112of the first wall110, the radially extended portion122of the second wall120, and the axial portions121of the second wall120together define the cavity115. In various embodiments, such as further depicted in regard toFIG. 6, the seal140is disposed into the second wall120and the first wall110together defining the cavity115.

Referring now toFIGS. 8-9, additional exemplary embodiments of portions of the combustor assembly50are further provided.FIG. 8provides an side view such as shown and described in regard toFIGS. 4-7.FIG. 9provides an exemplary top-down view of the side view generally provided in regard toFIG. 8. InFIG. 9, the deflector assembly100may generally include a plurality of first walls110arranged in adjacent arrangement around an annulus of the combustor assembly50. The seal140may be disposed between circumferentially adjacent (i.e., adjacent along circumferential direction C inFIG. 9) portions of the first wall110.

Referring toFIG. 9, the first wall110of the deflector assembly100may further define an opening111therethrough. The opening111may generally define a cooling orifice or shaped opening to permit a flow of air, shown via arrows85, to egress from the cavity115to the combustion chamber62. The opening111may generally provide thermal attenuation or cooling to the first wall110of the deflector assembly100.

Referring now toFIGS. 10-11, additional exemplary embodiments of portions of the combustor assembly50are further provided. The radially extended portion122of the second wall120is extended substantially along the radial direction R adjacent to the first wall110. The first wall110and the radially extended portion122of the second wall120may together define the cavity115therebetween.

Referring toFIG. 11, in one exemplary embodiment, the portion112of the first wall110may extend at an acute radial angle113relative to the longitudinal direction L. In various embodiments, the acute radial angle113may be between approximately 15 degrees and approximately 75 degrees relative to the fuel nozzle centerline13. In one embodiment, the acute radial angle113may be between approximately 30 degrees and approximately 60 degrees relative to the fuel nozzle centerline13.

Referring still toFIG. 11, the second wall120and the portion112of the first wall110may together define the cavity115therebetween. In various embodiments, the radially extended portion122of the second wall120and the portion112of the first wall110may together define the cavity115therebetween.

In still various embodiments, such as generally depicted inFIGS. 10-11, the second wall120and the first wall110may define the cavity115as a substantially serpentine passage. The cavity115defining the substantially serpentine passage may generally define one or more pinch points, flow turns, or other features inhibiting an amount of the flow of fluid83through the cavity115to flow to the combustion chamber62, such as generally depicted via arrows85.

Referring now toFIGS. 12-13, further exemplary embodiments of a portion of the combustor assembly50are generally provided. The embodiments shown in regard toFIGS. 12-13may be configured substantially similarly as shown and described in regard toFIGS. 4-11. However, inFIGS. 12-13, the combustor assembly50may further define the seal140as a labyrinth seal assembly. In one embodiment, such as depicted in regard toFIG. 12, the second wall120and the first wall110may together define the seal140as the labyrinth seal assembly. In another embodiment, such as depicted in regard toFIG. 13, the first wall110and the liner wall130may together define the seal140as the labyrinth seal assembly. Referring toFIGS. 12-13, the seal140

Referring now toFIG. 14, another exemplary embodiment of a portion of the combustor assembly50is generally provided. The embodiment shown in regard toFIG. 14may be configured substantially similarly as shown and described in regard toFIGS. 4-13. RegardingFIG. 14, in one embodiment, the second wall120may further define an opening124therethrough to permit a flow of fluid83therethrough to the cavity115. In various embodiments, the opening124may generally define a metering hole or orifice to control an amount of the flow of fluid83permitted therethrough and to the combustion chamber62, such as depicted via arrows85.

All or part of the combustor assembly50may 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 combustor50, including, but not limited to, the first wall110, the second wall120, the liner130, the seal140, 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 engine10and combustor assembly50generally shown and described herein may improve leakage control. The various embodiments described herein may limit leakage or flow variation across the deflector assembly100into the combustion chamber62. 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.