Abstract: An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe.

Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.

Abstract: A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

Abstract: A vane cluster for a gas turbine engine including an inner diameter platform and an outer diameter platform. A plurality of vanes span from the inner diameter platform to the outer diameter platform. An inbound region is defined between a first vane and a second vane of the plurality of vanes. A plenum is defined in the inner diameter platform at the inbound region. The plenum including a plurality of film cooling holes fluidly connecting the plenum to a primary flowpath. A feed hole connects the plenum to a core cooling cavity of one of the first vane and the second vane to the plenum.

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.

Abstract: A seal segment includes a flapper seal, a wire mesh acting as a hinge for the flapper seal, and a spring. The flapper seal has a first surface and a second surface. The wire mesh includes a first section connected to the first surface of the flapper seal and a second section connected to the first section. The spring includes a first end that is in contact with the first section of the wire mesh to apply pressure to the first surface of the flapper seal and a second end adjacent the second section of the wire mesh.

Abstract: A seal segment includes a flapper seal, a wire mesh acting as a hinge for the flapper seal, and a spring. The flapper seal has a first surface and a second surface. The wire mesh includes a first section connected to the first surface of the flapper seal and a second section connected to the first section. The spring includes a first end that is in contact with the first section of the wire mesh to apply pressure to the first surface of the flapper seal and a second end adjacent the second section of the wire mesh.

Abstract: A gas turbine engine nozzle includes a flap movable relative to a structure. A seal assembly is supported by one of the structure and the flap and includes a seal hinged about an axis. The seal has a sealing profile engaging a seal land of the other of the structure and the flap. A biasing member is configured to urge the hinged seal toward the seal land. A method of sealing a nozzle flap includes supporting a seal relative to a structure along an axis. The seal is urged toward a nozzle flap. The seal rotates about the axis to maintain engagement between the seal and the nozzle flap in response to the urging step.

Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.

Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.

Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.

Abstract: A seal segment includes a flapper seal, a wire mesh acting as a hinge for the flapper seal, and a spring. The flapper seal has a first surface and a second surface. The wire mesh includes a first section connected to the first surface of the flapper seal and a second section connected to the first section. The spring includes a first end that is in contact with the first section of the wire mesh to apply pressure to the first surface of the flapper seal and a second end adjacent the second section of the wire mesh.

Abstract: A flexible panel assembly for a gas turbine engine selectively exhibits a range of positions to regulate exhaust of the engine.

Abstract: A cooling system for a gas turbine engine includes a first structure movable relative to a second structure. The first structure has a cavity. A valve selectively controls fluid flow from a cooling source to the cavity. A valve is configured to move between first and second fluid flow positions in response to movement of the first structure. The first fluid flow position provides a greater amount of cooling fluid from the cooling source to the cavity than in the second fluid flow position.

Abstract: A cooling air flow ejector has a primary nozzle position to entrain air from a secondary nozzle. Mixed air is provided into a downstream flow conduit to be directed to an exhaust liner for a gas turbine engine. A variable area device controls a volume of air passing through a primary nozzle. A control for the variable area device to control the size of an orifice within the variable area device controls the volume of air reaching the exhaust liner to be cooled.

Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.

Abstract: An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe.

Abstract: A cooling system for a gas turbine engine includes a first structure movable relative to a second structure. The first structure has a cavity. A valve selectively controls fluid flow from a cooling source to the cavity. A valve is configured to move between first and second fluid flow positions in response to movement of the first structure. The first fluid flow position provides a greater amount of cooling fluid from the cooling source to the cavity than in the second fluid flow position.