Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween, the combustion chamber configured to receive an air-fuel mixture for combustion therein; and an insert including a body portion extending through the first liner, a shoulder circumscribing the body portion and abutting the first hot side, and an inlet portion coupled to the body portion and abutting the first cold side such that the inlet portion and the shoulder capture the second liner therebetween to retain the insert.

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber therewith. The outer liner is a dual walled liner with a first wall and a second wall. A fuel igniter includes a tip portion configured to ignite an air and fuel mixture in the combustion chamber. An igniter support assembly positions the fuel igniter relative to the combustion chamber. The igniter support assembly defines a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter. The igniter support assembly includes first and second floating seals that are configured to accommodate radial and axial relative movements.

Abstract: A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.

Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber.

Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends. A first liner seal is configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions.

Abstract: A combustor is provided for a turbine engine. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The combustor further includes an insert having a body portion extending through the first liner and terminating at a tip, the body portion configured to direct air flow into the combustion chamber. The insert further includes a cooling hole defined in the body portion and configured to direct a first portion of the air flow toward the tip as cooling air.

Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween, the combustion chamber configured to receive an air-fuel mixture for combustion therein; and an insert including a body portion extending through the first liner, a shoulder circumscribing the body portion and abutting the first hot side, and an inlet portion coupled to the body portion and abutting the first cold side such that the inlet portion and the shoulder capture the second liner therebetween to retain the insert.

Abstract: A combustor for a turbine engine includes a hot wall and a cold wall forming a dual walled liner and a liner cavity with the hot wall. The cold wall defines a plurality of impingement cooling holes configured to deliver an impingement cooling flow. A first downstream end terminates the hot wall and is configured to receive the impingement cooling flow from the plurality of impingement cooling holes, and a second downstream end terminates the cold wall and is longer in a generally downstream direction than the first downstream end. A combustion chamber is formed with the dual walled liner and the liner and faces an opposite side of the hot wall relative to the combustion chamber. The combustion chamber has a longitudinal axis and is configured to receive an air-fuel mixture in the generally downstream direction along the longitudinal axis.

Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends. A first liner seal is configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions.

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber therewith. The outer liner is a dual walled liner with a first wall and a second wall. A fuel igniter includes a tip portion configured to ignite an air and fuel mixture in the combustion chamber. An igniter support assembly positions the fuel igniter relative to the combustion chamber. The igniter support assembly defines a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter. The igniter support assembly includes first and second floating seals that are configured to accommodate radial and axial relative movements.

Abstract: A dual wall structure for a combustor of a gas turbine engine including an inner liner and an outer liner coupled to a combustor dome and defining a combustion chamber there between. Each of the inner liner and the outer liner include an outer wall and an inner wall. Each of the outer walls includes a plurality of impingement holes formed therein for allowing a coolant to flow therethrough. Each of the inner walls is coupled to the outer wall via a plurality of threaded studs and includes a plurality of forward heat shield panels and a plurality of aft heat shield panels. Each of the plurality of forward heat shield panels and aft heat shield panels includes a plurality of side rails, a forward rail, and an aft rail including a plurality of controlled openings, that when coupled to the outer wall defines a single cavity there between. A plurality of cavities being formed by the plurality of forward and aft heat shield panels.

Abstract: A dual wall structure for a combustor of a gas turbine engine including an inner liner and an outer liner coupled to a combustor dome and defining a combustion chamber there between. Each of the inner liner and the outer liner include an outer wall and an inner wall. Each of the outer walls includes a plurality of impingement holes formed therein for allowing a coolant to flow therethrough. Each of the inner walls is coupled to the outer wall and a combustor dome and includes a plurality of heat shield panels. Each of the plurality of heat shield panels extends a longitudinal length of the combustor chamber and includes a plurality of side rails, an aft rail and a forward flange that when coupled to the outer wall defines a single cavity there between. A plurality of cavities being formed by the plurality of heat shield panels.