Abstract: An additively-manufactured component may include a support structure comprising an array of support members, and a component body integrally formed with the support structure. The array of support members may include a plurality of conduction gates. Respective ones of the plurality of conduction gates may define a portion of a corresponding support member that has a reduced unit area and that provides resistance to thermal conduction through the corresponding support member. The plurality of conduction gates may be respectively located at a plurality of locations along a vertical axis of the support structure.

Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.

Abstract: An additively-manufactured component may include a support structure comprising an array of support members, and a component body integrally formed with the support structure. The array of support members may include a plurality of conduction gates. Respective ones of the plurality of conduction gates may define a portion of a corresponding support member that has a reduced unit area and that provides resistance to thermal conduction through the corresponding support member. The plurality of conduction gates may be respectively located at a plurality of locations along a vertical axis of the support stricture.

Abstract: Additively manufactured components include a support structure and a component body integrally formed with the support structure using an additive-manufacturing process. The support structure includes an array of support members and at least some of the support members have a conduction gate such that the array of support members includes conduction gates distributed at a multitude of locations along the vertical axis of the respective support members. Methods of securing a body of a component to a build platform during additive manufacturing include forming a support structure and a component body integrally with the support structure using the additive-manufacturing process, in which the support structure includes an array of support members and at least some of the support members have a conduction gate such that the array of support members includes conduction gates distributed at a multitude of locations along the vertical axis of the respective support members.

Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner that at least partially define a combustion chamber. The annular dome defines a plurality of circumferentially spaced fuel injection ports and a plurality of mounting assemblies are configured for receiving and supporting a plurality of fuel injector assemblies within the fuel injection ports. Each mounting assembly includes a ferrule positioned adjacent to and extending around a peripheral edge of the respective fuel injection port. A spring finger is coupled to an interior surface of the ferrule and extends toward a centerline of the fuel injection port to form a seal with the fuel injector assembly.

Abstract: Additively manufactured components include a support structure and a component body integrally formed with the support structure using an additive-manufacturing process. The support structure includes an array of support members and at least some of the support members have a conduction gate such that the array of support members includes conduction gates distributed at a multitude of locations along the vertical axis of the respective support members. Methods of securing a body of a component to a build platform during additive manufacturing include forming a support structure and a component body integrally with the support structure using the additive-manufacturing process, in which the support structure includes an array of support members and at least some of the support members have a conduction gate such that the array of support members includes conduction gates distributed at a multitude of locations along the vertical axis of the respective support members.

Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.

Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner that at least partially define a combustion chamber. The annular dome defines a plurality of circumferentially spaced fuel injection ports and a plurality of mounting assemblies are configured for receiving and supporting a plurality of fuel injector assemblies within the fuel injection ports. Each mounting assembly includes a ferrule positioned adjacent to and extending around a peripheral edge of the respective fuel injection port. A spring finger is coupled to an interior surface of the ferrule and extends toward a centerline of the fuel injection port to form a seal with the fuel injector assembly.

Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.

Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.