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.
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;
a moveable interface comprising a fork end defining a cavity and a head end, wherein the aft end of the first liner is positioned in the cavity; and
a spring positioned in the cavity, wherein the moveable interface is coupled to the aft end of the first liner via the spring.
2. The combustor assembly of claim 1 , 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 claim 2 , wherein the second liner is cantilevered from the turbine nozzle.
4. The combustor assembly of claim 1 , wherein the gap is extended annularly along the circumferential direction.
5. The combustor assembly of claim 1 , wherein the moveable interface abuts the second liner at a forward end of the second liner.
6. The combustor assembly of claim 5 , wherein the head end is positioned proximate to the forward end of the second liner relative to the fork end of the moveable interface, and wherein the fork end is proximate to the aft end of the first liner relative to the head end.
7. The combustor assembly of claim 5 , wherein the moveable interface forms an opening providing fluid communication between a cavity and a compressor discharge plenum surrounding the combustor assembly.
8. The combustor assembly of claim 5 , wherein the moveable interface is extended annularly in the gap between the first liner and the second liner.
9. The combustor assembly of claim 5 , 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.
10. The combustor assembly of claim 9 , wherein the moveable interface comprises two or more members.
11. The combustor assembly of claim 9 , 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.
12. The combustor assembly of claim 1 , wherein the spring is extended along the longitudinal direction from the first liner toward the second liner.
13. The combustor assembly of claim 1 , wherein the spring is configured to push the moveable interface along the longitudinal direction toward the second liner.
14. The combustor assembly of claim 1 , the combustor assembly comprising:
a seal positioned in the cavity, wherein the moveable interface is further coupled to the first liner via the seal.
15. The combustor assembly of claim 14 , wherein the seal is extended annularly along the first liner.
16. The combustor assembly of claim 14 , wherein the seal is coupled to a cold side of the first liner.
17. 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, the combustor assembly further comprising
a moveable interface comprising a fork end defining a cavity and a head end,
wherein an aft end of the first liner is positioned in the cavity; and
a spring positioned in the cavity, wherein the moveable interface is coupled to the aft end of the first liner via the spring; and
a turbine nozzle at a downstream end of the combustion chamber, wherein the second liner is connected to the turbine nozzle.