Combustor assembly with moveable interface dilution opening

A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.

FIELD

The present disclosure generally pertains to gas turbine engines, and, more specifically, to a combustor for a gas turbine engine.

BACKGROUND

Gas turbine engines generally include combustion sections configured to generate combustion gases from a receive a flow of compressed air mixed with fuel and ignited in a combustion chamber. This process generates heat and pressure changes that require flows of air to condition the combustion gases for a downstream turbine section, or to limit damage to the combustion section due to the generated heat.

Combustion sections are generally required to produce high-energy combustion gases while also limiting emissions such as oxides of nitrogen, greenhouse gases, unburned hydrocarbons, or smoke. Furthermore, combustion sections are challenged to introduce cooling air to limit damage or deterioration to structures at the combustion section and downstream turbine section. Generally, achieving some of these challenges requires or results in compromises toward achieving other challenges. Furthermore, it is recognized that changes in geometries at a combustion section often have unpredictable effects at the combustion section, such as with regard to limiting emissions, limiting deterioration, or limiting undesired pressure oscillations.

As such, there is a need for improved combustion section structures. Furthermore, there is a need for improved combustion gas dilution structures that limit deterioration of combustion section structures.

BRIEF DESCRIPTION

Aspects and advantages of the disclosure 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 disclosure.

Aspects of the present disclosure are directed to a gas turbine engine and combustor assembly. The combustor assembly includes a first liner and a second liner together defining at least in part a combustion chamber. The first liner and the second liner are separated by a gap along the longitudinal direction. The first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction. The gap is extended along the circumferential direction.

Another aspect of the present disclosure is directed to a gas turbine engine defining a longitudinal direction and a circumferential direction. The gas turbine engine includes a combustor assembly having a first liner and a second liner together defining at least in part a combustion chamber. The first liner and the second liner are separated by a gap along the longitudinal direction. The first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction. The gap is extended along the circumferential direction. The combustor assembly includes a bulkhead assembly at an upstream end of the combustion chamber. The first liner is connected to the bulkhead assembly. A turbine nozzle is positioned at a downstream end of the combustion chamber, and the second liner is connected to the turbine nozzle.

DETAILED DESCRIPTION

Additionally, the terms “low,” “high,” or their respective comparative degrees (e.g., lower, higher, where applicable) each refer to relative speeds within an engine, unless otherwise specified. For example, a “low-pressure turbine” operates at a pressure generally lower than a “high-pressure turbine.” Alternatively, unless otherwise specified, the aforementioned terms may be understood in their superlative degree. For example, a “low-pressure turbine” may refer to the lowest maximum pressure turbine within a turbine section, and a “high-pressure turbine” may refer to the highest maximum pressure turbine within the turbine section.

The present subject matter is directed to a combustor for a gas turbine engine. In general, the combustor can include a forward liner segment and an aft liner segment positioned downstream of the forward liner segment relative to a flow of fluid along a longitudinal direction toward an exhaust section. In this respect, the forward and aft liner segments at least partially define a combustion chamber in which a fuel and air mixture is burned to generate combustion gases.

A dilution slot or gap is formed by a longitudinal separation of the forward liner segment and the aft liner segment. The gap allows for up to a substantially 360 degree sheet of dilution fluid, such as compressed air, to enter the combustion chamber for rapid mixing with the combustion gases and improved completion of the combustion process in a lean zone. An annular wall or fence is extended radially into the combustion chamber from the aft liner segment, allowing for improved penetration of the compressed air into the combustion chamber.

In certain embodiments, the forward liner segment is connected to an upstream bulkhead assembly and the aft liner segment is connected to a downstream turbine nozzle. The forward liner segment may be cantilevered from the bulkhead assembly. The aft liner segment may be cantilevered from the turbine nozzle. The dilution slot or gap is formed between the cantilevered ends of the forward liner segment and the aft liner segment.

In a particular arrangement, a moveable interface is positioned between forward liner segment and the aft liner segment. The moveable interface may form a floating insert that regulates or controls a longitudinal dimension of the gap and accommodates the independent thermal expansion of the forward and aft liner segments.

Embodiments provided herein allow for reducing emissions, such as oxides of nitrogen (NOx) in rich-burn combustor configurations. The dilution slot or gap formed by forward and aft liner segments, such as a substantially or fully annular gap, may substantially reduce gas temperatures along the walls of the liners by 500 degrees Fahrenheit or more. Additionally, or alternatively, embodiments provided herein may reduce a circumferential temperature gradient at and downstream of the combustion chamber (i.e., hot spots) and generally improve pattern factor, allowing for improved durability and reduced deterioration of the liners and downstream turbine section. The moveable interface may further allow for adjustment or controllability of the gap relative to changes in liner temperature and provide improved vibration response or dampening.

Referring now to the drawings,FIG.1is a schematic cross-sectional view of one embodiment of a gas turbine engine10. In the illustrated embodiment, the engine10is configured as a high-bypass turbofan engine. However, in alternative embodiments, the engine10may be configured as a propfan engine, a turbojet engine, a turboprop engine, a turboshaft gas turbine engine, or any other suitable type of gas turbine engine.

As shown inFIG.1, the engine10defines a longitudinal direction L, a radial direction R, and a circumferential direction C. In general, the longitudinal direction L extends parallel to a longitudinal centerline12of the engine10, the radial direction R extends orthogonally outward from the longitudinal centerline12, and the circumferential direction C extends generally concentrically around the longitudinal centerline12.

In general, the engine10includes a fan14, a low-pressure (LP) spool16, and a high pressure (HP) spool18at least partially encased by an annular nacelle20. More specifically, the fan14may include a fan rotor22and a plurality of fan blades24(one is shown) coupled to the fan rotor22. In this respect, the fan blades24are spaced apart from each other along the circumferential direction C and extend outward from the fan rotor22along the radial direction R. Moreover, the LP and HP spools16,18are positioned downstream from the fan14along the longitudinal centerline12(i.e., in the longitudinal direction L). As shown, the LP spool16is rotatably coupled to the fan rotor22, thereby permitting the LP spool16to rotate the fan14. Additionally, a plurality of outlet guide vanes or struts26spaced apart from each other in the circumferential direction C extend between an outer casing28surrounding the LP and HP spools16,18and the nacelle20along the radial direction R. As such, the struts26support the nacelle20relative to the outer casing28such that the outer casing28and the nacelle20define a bypass airflow passage30positioned therebetween.

The outer casing28generally surrounds or encases, in serial flow order, a compressor section32, a combustion section34, a turbine section36, and an exhaust section38. For example, in some embodiments, the compressor section32may include a low-pressure (LP) compressor40of the LP spool16and a high-pressure (HP) compressor42of the HP spool18positioned downstream from the LP compressor40along the longitudinal centerline12. Each compressor40,42may, in turn, include one or more rows of stator vanes44interdigitated with one or more rows of compressor rotor blades46. Moreover, in some embodiments, the turbine section36includes a high-pressure (HP) turbine48of the HP spool18and a low-pressure (LP) turbine50of the LP spool16positioned downstream from the HP turbine48along the longitudinal centerline12. Each turbine48,50may, in turn, include one or more rows of stator vanes52interdigitated with one or more rows of turbine rotor blades54. In a particular embodiment, the turbine section includes a first stator vane assembly or turbine nozzle52positioned downstream of a combustion chamber106and upstream of the turbine rotor blades54.

Additionally, the LP spool16includes the low-pressure (LP) shaft56and the HP spool18includes a high pressure (HP) shaft58positioned concentrically around the LP shaft56. In such embodiments, the HP shaft58rotatably couples the rotor blades54of the HP turbine48and the rotor blades46of the HP compressor42such that rotation of the HP turbine rotor blades54rotatably drives HP compressor rotor blades46. As shown, the LP shaft56is directly coupled to the rotor blades54of the LP turbine50and the rotor blades46of the LP compressor40. Furthermore, the LP shaft56is coupled to the fan14via a gearbox60. In this respect, the rotation of the LP turbine rotor blades54rotatably drives the LP compressor rotor blades46and the fan blades24.

In several embodiments, the engine10may generate thrust to propel an aircraft. More specifically, during operation, air62enters an inlet portion64of the engine10. The fan14supplies a first portion (indicated by arrow66) of the air62to the bypass airflow passage30and a second portion (indicated by arrow68) of the air62to the compressor section32. The second portion68of the air62first flows through the LP compressor40in which the rotor blades46therein progressively compress the second portion68of the air62. Next, the second portion68of the air62flows through the HP compressor42in which the rotor blades46therein continue progressively compressing the second portion68of the air62. The compressed second portion68of the air62is subsequently delivered to the combustion section34. In the combustion section34, the second portion68of the air62mixes with fuel and burns to generate high-temperature and high-pressure combustion gases70. Thereafter, the combustion gases70flow through the HP turbine48which the HP turbine rotor blades54extract a first portion of kinetic and/or thermal energy therefrom. This energy extraction rotates the HP shaft58, thereby driving the HP compressor42. The combustion gases70then flow through the LP turbine50in which the LP turbine rotor blades54extract a second portion of kinetic and/or thermal energy therefrom. This energy extraction rotates the LP shaft56, thereby driving the LP compressor40and the fan14via the gearbox60. The combustion gases70then exit the engine10through the exhaust section38.

The configuration of the gas turbine engine10described above and shown inFIG.1is provided only to place the present subject matter in an exemplary field of use. Thus, the present subject matter may be readily adaptable to any manner of gas turbine engine configuration, including other types of aviation-based gas turbine engines, marine-based gas turbine engines, and/or land-based/industrial gas turbine engines.

FIG.2is a cross-sectional view of one embodiment of the combustion section34of the gas turbine engine10. As shown, the combustion section34includes an annular combustor assembly100. In several embodiments, the combustion section34includes a compressor discharge casing118. In such embodiments, the compressor discharge casing118at least partially surrounds or otherwise encloses the combustor(s)100in the circumferential direction C. In this respect, a compressor discharge plenum120is defined between the compressor discharge casing118and liners102,104. The compressor discharge plenum120is, in turn, configured to supply compressed air to the combustor(s)100. Specifically, as shown, the air68exiting the HP compressor42is directed into the compressor discharge plenum120by an inlet guide vane122. The air68within the compressor discharge plenum120is then supplied to the combustion chamber(s)106of the combustor(s)100by the fuel nozzle(s)112for use in combusting the fuel.

The combustor assembly100includes an inner liner102extended annularly along the circumferential direction C. The combustor assembly100further includes an outer liner104positioned outward from the inner liner102along the radial direction R. The outer liner104is extended annularly along the circumferential direction C. In this respect, the inner and outer liners102,104define a combustion chamber106therebetween. Each liner102,104includes a first liner or forward liner segment108and a second liner or aft liner segment110positioned downstream of the forward liner segment108relative to the direction of flow of fluid, such as the flow of the combustion gases70, through the combustor assembly100. The combustor assembly100includes one or more fuel nozzles112extended through a bulkhead assembly107providing a wall at an upstream end121of the combustion chamber106. The fuel nozzle112supplies a mixture of gaseous and/or liquid fuel and oxidizer, such as air68, to the combustion chamber106. The fuel and air mixture burns within the combustion chamber106to generate the combustion gases70. AlthoughFIG.2illustrates a single annular combustor assembly100, the combustion section34may, in other embodiments, include a plurality of combustor assemblies100. Other combustor configurations include can-combustors and can-annular combustors.

In several embodiments, the combustor assembly100includes a dilution slot or gap114formed by a separation along the longitudinal direction L of the forward liner segment108from the aft liner segment110. The dilution slot or gap114is extended at least partially along the circumferential direction C. The forward liner segment108is extended from the bulkhead assembly107along the longitudinal direction L toward a downstream end123of the combustion chamber106. The aft liner segment110is extended from the turbine nozzle52along the longitudinal direction L toward the upstream end121of the combustion chamber106.

In a particular embodiment, the forward liner segment108is cantilevered from the bulkhead assembly107and the aft liner segment110is cantilevered from the turbine nozzle52. Referring now toFIGS.2-3, the dilution slot or gap114is positioned between an aft end128of the forward liner segment108and a forward end127of the aft liner segment110. In certain embodiments, the forward end127of the aft liner segment110proximate to the dilution slot or gap114includes a radially-extended wall or fence116. The fence116is positioned adjacent to the dilution slot or gap114and is extended into the combustion chamber106. The fence116may furthermore extend annularly along the circumferential direction C. In certain embodiments, the fence116may include a plurality of segmented arcs forming a partially or substantially annular structure.

Referring back toFIG.2, during operation, a portion of the compressed air, depicted schematically via arrows71, is routed around the combustor assembly100through the compressor discharge plenum120. At least a portion of the compressed air enters into the combustion chamber106through the gap114, such as depicted schematically via arrows72. The dilution air72entering the combustion chamber106through the gap114reduces or mitigates the formation of NOR. Furthermore, the fence116directs the dilution air72along radial direction R toward the center of the combustion chamber106and increases the turbulence within the combustion chamber106, allowing for improved mixing of the dilution air72with the combustion gases70to mitigate the formation of NOR. It should be appreciated that particular embodiments include the fence116extended inward along the radial direction R toward the center of the combustion chamber106from the outer liner104. In still particular embodiments, the fence116is extended outward along the radial direction R toward the center of the combustion chamber106from the inner liner102.

Referring now toFIG.4throughFIG.16, in various embodiments, the combustor assembly100includes a moveable interface115abutting the aft liner segment110at the forward end127. The moveable interface surrounds the aft end128of the forward liner segment108. In certain embodiments, such as further described herein, the moveable interface115is coupled to the aft end128of the forward liner segment108. In a particular embodiment, the moveable interface115is detachably coupled to the forward end127of the aft liner segment110. However, it should be appreciated that a head end117of the moveable interface115may be brazed, welded, or otherwise mated to the aft liner segment110.

The moveable interface115includes the head end117proximate to the forward end127of the aft liner segment110. The moveable interface115includes a fork end119proximate to the aft end128of the forward liner segment108. The fork end119is proximate to the aft end128of the forward liner segment108relative to the head end117that is distal to the fork end119and proximate to the forward end127of the aft liner segment110. The head end117forms a terminal end configured to abut the forward end127of the aft liner segment110along the longitudinal direction L. The fork end119branches into one or more longitudinally-extended segments at least partially surrounding the aft end128of the forward liner segment108. The fork end119forms a cavity129at which the aft end128of the forward liner segment108is positioned.

In certain embodiments, the fork end119and the head end117are connected by a member124extended along the longitudinal direction L. The moveable interface115may include two or more members124extended across the gap114. Each member124is separated along the circumferential direction C, such as to separate the substantially annular dilution slot or gaps114into arcuate sections. Each arcuate section of dilution slot or gap114is extended between 2 degrees and 178 degrees along the circumferential direction C. In various embodiments, the moveable interface115forms a plurality of arcuate sections forming a substantially annular or 360 degree gap114. It should be appreciated that the substantially annular gap114including the members124may form up to 359 degrees of space or opening, or at least 345 degrees of opening between the liners108,110.

In certain embodiment, such as depicted inFIG.4, a spring130is positioned in the cavity129. The moveable interface115is coupled to the aft end128of the forward liner segment108via the spring130. In various embodiments, the spring130is extended along the longitudinal direction L (FIG.2) or substantially co-directional to the flow of combustion gases70through the combustion chamber106from the forward liner segment108toward the aft liner segment110. The spring130is configured to push the moveable interface115along the longitudinal direction L toward the aft liner segment110. As such, the spring130may allow the moveable interface115to expand, contract, or otherwise move along the longitudinal direction L, such as to allow for movement based on changes in temperature, or differences in temperature between components, such as the forward liner segment108and the aft liner segment110. The spring130may prevent undesired stresses and fatigue associated with thermal cycling and thermal gradients across the combustor assembly100. Furthermore, the spring130may allow the moveable interface115to adjust or control the gap114relative to changes in liner temperature, or changes in a difference between temperatures at the forward liner segment108and the aft liner segment110. The spring130may further provide improved vibration response or dampening.

In various embodiments, the spring130is extended circumferentially within the cavity129. The spring130may form a single annular piece, or include a plurality of segments or arcs. The spring130may further form a seal at the cavity129mitigating flow through the cavity129between the compressor discharge plenum120and the combustion chamber106.

In certain embodiments, such as depicted inFIGS.5-10, the combustor assembly100additionally, or alternatively, includes a seal132positioned in the cavity129to mitigate flow through the cavity129between the compressor discharge plenum120and the combustion chamber106. The seal132may include a single annular piece extended circumferentially through the cavity129. In other embodiments, the seal may include a plurality of segments or arcs in circumferentially adjacent arrangement. The seal may include a rope seal, a piston ring, a spring (e.g., an annular member detached at a terminal end), a gasket, or other appropriate sealing device. In a particular embodiment, the moveable interface115is coupled to the forward liner segment108via the seal132. In certain embodiments, the forward liner segment108attaches to the moveable interface115via the seal132and/or the spring130. The seal132may extend annularly along the forward liner segment108. In a still particular embodiment, the seal132is coupled to a cold side of the forward liner segment108, such as the face proximate to the compressor discharge plenum120and distal to the combustion chamber106.

Referring still toFIGS.5-10, in various embodiments, the head end117of the moveable interface115is extended along the radial direction R. The head end117may particularly extend alongside the fence116. In certain embodiments, such as depicted inFIGS.8-10, the head end117is extended outward along the radial direction R. In certain embodiments, the head end117is extended annularly along the circumferential direction C. The members124are connected to the head end117and raised above the gap114. The members124positioned as such may decrease or mitigate aerodynamic interactions of the dilution air72relative to the dilution air72entering the combustion chamber106. Stated differently, when the members124are positioned further away from the combustion chamber106, the flow characteristics of the dilution air72entering the combustion chamber106may be more circumferentially uniform. In still various embodiments, the member124may be utilized to desirably alter or condition the flow characteristics of the dilution air72when mixing with the combustion gases70.

Referring briefly toFIG.10, another exemplary embodiment of the moveable interface115is provided. The combustor assembly100is configured substantially similarly as depicted and described in regard toFIGS.1-9. InFIG.10, the fork end119may further form a vent opening125providing fluid communication between the compressor discharge plenum120and the cavity129. The vent opening125may be formed as a plurality of discrete openings in adjacent arrangement along the circumferential direction C. The vent opening125may be a slot extended along an arc or circumferential segment, or as a substantially round orifice, or other suitable opening. The vent opening125may allow for a desired amount of cooling fluid through the cavity129, such as to decrease the temperature within the cavity129, or at the fork end119, or other portions of the moveable interface115proximate thereto.

Referring now toFIGS.11-16, exemplary embodiments of the moveable interface115, the forward liner segment108, and the aft liner segment110are provided. The exemplary embodiments provided in regard toFIGS.11-16are configured substantially similarly as depicted and described in regard to one or more ofFIGS.2-10. InFIG.11, the moveable interface115includes a plurality of members124including the head end117, in which each head end117is separate from one another along the circumferential direction C.

InFIGS.12-13, the exemplary embodiments provided are configured substantially similarly as depicted and described in regard to one or more ofFIGS.2-10. InFIGS.12-13, various exemplary geometries of the head end117abutting the second liner110are provided. InFIG.12, the head end117includes a substantially “T” geometry, at which a portion of the head end117is extended inward and outward along the radial direction R. InFIG.13, the head end117is extended inward along the radial direction R and abutting the fence116. InFIG.13, the second liner110may be offset along the radial direction R from the first liner108. In a particular embodiment, the second liner110is offset outward along the radial direction R from the first liner108, and the member124is connected to a radially outward portion of the fork end119to place the first liner108relatively radially inward in the within the fork end119. However, it should be appreciated that other embodiments may offset the second liner110inward along the radial direction R from the first liner108via the member124connected to a radially inward portion of the fork end119to place the first liner108relatively radially outward within the fork end119.

InFIGS.14-15, the member124may further include one or more bends or radii126, such as to form a spring between the head end117of the moveable interface115and the fork end119. In a particular embodiment, the member124may include a first material having a first thermal coefficient of expansion different from the head end117and/or the fork end119having a second material having a second thermal coefficient of expansion. The first thermal coefficient of expansion may be configured to allow for substantially greater change or movement relative to the second coefficient of expansion. Still further, the member124having one or more bends or radii126may form a spring at the moveable interface115, such as to allow for controllability or adjustment of the gap114and/or improved vibration response and dampening such as described above.

InFIG.16, a perspective view is provided in which the seal132and the spring130are each included in the cavity129, such as described above. The moveable interface115may include a plurality of the spring positioned in the cavity129at various circumferential portions. The seal132may be extended annularly, such as to inhibit flow between the compressor discharge plenum120and the cavity129. In still another embodiment, the moveable interface115may include the vent opening125, such as depicted and described in regard toFIG.10. The vent opening may allow a controlled or metered flow of fluid into the cavity129from the compressor discharge plenum120. In certain embodiments, the positioning of the vent opening125may correspond to a positioning of discrete springs130, such as to allow for a controlled magnitude of cooling fluid to thermally communicate from the compressor discharge plenum120to the spring130.

The combustor assembly100provided herein may be formed in part, in whole, or in some combination of materials including but not limited to pure metals, nickel alloys, chrome alloys, titanium, titanium alloys, magnesium, magnesium alloys, aluminum, aluminum alloys, and nickel or cobalt based superalloys (e.g., those available under the name Inconel® available from Special Metals Corporation), composite materials, metal matrix composites, or ceramic matrix composites (CMC), or combinations thereof, or other materials suitable for high-stress, high-temperature environments. In certain embodiments, the first liner or forward liner segment108and the second liner or aft liner segment110are each formed from sheet metal, castings, forgings, layups, additive manufacturing processes, or other appropriate manufacturing processes for combustors. The liners and respective components such as described herein may be formed as respective integral portions, or fastened, bonded, or otherwise formed together as may be appropriate for combustors and turbine sections. In still various embodiments, the forward liner segment108may include a first material, the aft liner segment110may include a second material, and the moveable interface115may include a third material, in which each material includes different thermal expansion coefficients from one another. The moveable interface115may form a floating insert that regulates or controls a longitudinal dimension of the gap114and accommodates the independent thermal expansion of the forward liner segment108and the aft liner segment110.

1. A combustor assembly defining a longitudinal direction and a circumferential direction, the combustor assembly comprising a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.

2. The combustor assembly of any one or more clauses herein, wherein the second liner is connected to a turbine nozzle at a downstream end of the combustion chamber, and wherein the first liner is connected to a bulkhead assembly at an upstream end of the combustion chamber.

3. The combustor assembly of any one or more clauses herein, wherein the second liner is cantilevered from the turbine nozzle.

4. The combustor assembly of any one or more clauses herein, wherein the gap is extended annularly along the circumferential direction.

5. The combustor assembly of any one or more clauses herein, the combustor assembly comprising a moveable interface abutting the second liner at a forward end, wherein the moveable interface surrounds an aft end of the first liner.

6. The combustor assembly of any one or more clauses herein, wherein the moveable interface is coupled to the aft end of the first liner.

7. The combustor assembly of any one or more clauses herein, wherein the moveable interface comprises a head end proximate to the forward end of the second liner relative to a fork end, and wherein the fork end is proximate to the aft end of the first liner relative to the head end.

8. The combustor assembly of any one or more clauses herein, wherein the aft end of the first liner is positioned in a cavity defined by the fork end of the moveable interface.

9. The combustor assembly of any one or more clauses herein, the combustor assembly comprising a spring positioned in the cavity, wherein the moveable interface is coupled to the aft end of the first liner via the spring.

10. The combustor assembly of any one or more clauses herein, wherein the spring is extended along the longitudinal direction from the first liner toward the second liner.

11. The combustor assembly of any one or more clauses herein, wherein the spring is configured to push the moveable interface along the longitudinal direction toward the second liner.

12. The combustor assembly of any one or more clauses herein, the combustor assembly comprising a seal positioned in the cavity, wherein the moveable interface is coupled to the first liner via the seal.

13. The combustor assembly of any one or more clauses herein, wherein the seal is extended annularly along the first liner.

14. The combustor assembly of any one or more clauses herein, wherein the seal is coupled to a cold side of the first liner.

15. The combustor assembly of any one or more clauses herein, wherein the moveable interface comprises a member extended along the longitudinal direction, wherein the member comprises a head end proximate to the forward end of the second liner, and wherein the member comprises a fork end proximate to the aft end of the first liner.

16. The combustor assembly of any one or more clauses herein, wherein the moveable interface comprises two or more members.

17. The combustor assembly of any one or more clauses herein, wherein the first liner and the second liner are each extended annularly, and wherein the member forms the gap as an arcuate section, wherein the arcuate section is extended between 2 degrees and 178 degrees along the circumferential direction.

18. The combustor assembly of any one or more clauses herein, wherein the first liner, the second liner, and the moveable interface are separable from one another.

19. The combustor assembly of any one or more clauses herein, wherein the moveable interface forms an opening providing fluid communication between the cavity and a compressor discharge plenum surrounding the combustor assembly.

20. The combustor assembly of any one or more clauses herein, wherein the moveable interface is extended annularly in the gap between the first liner and the second liner.

21. A gas turbine engine defining a longitudinal direction and a circumferential direction, the gas turbine engine comprising a combustor assembly comprising a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction, and wherein the combustor assembly comprises a bulkhead assembly at an upstream end of the combustion chamber, wherein the first liner is connected to the bulkhead assembly; and a turbine nozzle at a downstream end of the combustion chamber, wherein the second liner is connected to the turbine nozzle.

22. A gas turbine engine comprising the combustor assembly of any one or more clauses herein.