Abstract: A blade has an airfoil having a tip. The blade has a metallic substrate and a coating system atop the substrate at the tip. The coating system has: a first layer of at least 99.0% weight nickel; an abrasive layer having a matrix and an abrasive at least partially embedded in the matrix; and a second layer between the first layer and the matrix. The second layer is tougher or more ductile than at least one of the first layer and the matrix.

Abstract: Disclosed is an outer air seal, having: an axial member, the axial member extending axially from an axial front end to an axial aft end, and extending radially from a radial inner surface to a radial outer surface; a radial flange extending radially from the radial outer surface of the axial member to a radial outer tip, and extending axially from an axial front surface to an axial aft surface; and a first kerf slot defined through the axial member from the axial front end to the axial aft end and from the radial inner surface to the radial outer surface, and through the radial flange from the axial front surface to the axial aft surface, wherein a radial top end of the first kerf slot is radially spaced apart from the radial outer tip of the radial flange.

Abstract: Disclosed is an outer air seal, having: an axial member, the axial member extending axially from an axial front end to an axial aft end, and extending radially from a radial inner surface to a radial outer surface; a radial flange extending radially from the radial outer surface of the axial member to a radial outer tip, and extending axially from an axial front surface to an axial aft surface; and a first kerf slot defined through the axial member from the axial front end to the axial aft end and from the radial inner surface to the radial outer surface, and through the radial flange from the axial front surface to the axial aft surface, wherein a radial top end of the first kerf slot is radially spaced apart from the radial outer tip of the radial flange.

Abstract: A rotating assembly of a gas turbine engine includes a first rotating component; and a second rotating component located radially outboard of the first rotating component, relative to an engine central longitudinal axis. A seal assembly is configured to seal between the first rotating component and the second rotating component. The seal assembly includes a shuttle located on a radial outer surface of the second component and freely axially movable along the radial outer surface and a piston ring seal retained in the shuttle and engaged with the first rotating component. Axial motion of the first rotating component relative to the second rotating component urges movement of the shuttle along the radial outer surface of the second rotating component, while the position of the piston ring seal remains stationary relative to the first rotating component.

Abstract: A rotating assembly of a gas turbine engine includes a first rotating component; and a second rotating component located radially outboard of the first rotating component, relative to an engine central longitudinal axis. A seal assembly is configured to seal between the first rotating component and the second rotating component. The seal assembly includes a shuttle located on a radial outer surface of the second component and freely axially movable along the radial outer surface and a piston ring seal retained in the shuttle and engaged with the first rotating component. Axial motion of the first rotating component relative to the second rotating component urges movement of the shuttle along the radial outer surface of the second rotating component, while the position of the piston ring seal remains stationary relative to the first rotating component.

Abstract: An insert is disposable between an exterior surface of an annular body and an annular flange and between a support wall supportive of the annular flange and surface features of the exterior surface. The insert includes a forward section sized to fit between and to extend along respective arc-segments of the exterior surface and the annular flange and an aft section. The forward section includes a first end wall abuttable with the support wall, a second end wall and inner and outer diameter surfaces that extend between the first and second end walls for abutment with the exterior surface and the annular flange, respectively. The aft section extends from the second end wall to be engageable with the surface features.

Abstract: A blade has an airfoil having a tip. The blade has a metallic substrate and a coating system atop the substrate at the tip. The coating system has: a first layer of at least 99.0% weight nickel; an abrasive layer having a matrix and an abrasive at least partially embedded in the matrix; and a second layer between the first layer and the matrix. The second layer is tougher or more ductile than at least one of the first layer and the matrix.

Abstract: A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter operable to drive rotation of a starting spool of the gas turbine engine and a starter air valve operable to deliver compressed air to the air turbine starter in response to the starter air valve being open. The system also includes a metered orifice coupled in a bypass configuration around the starter air valve to deliver a reduced amount of the compressed air to the air turbine starter while the starter air valve is closed. The reduced amount of the compressed air delivered to the air turbine starter limits a motoring speed of the gas turbine engine below a resonance speed of the starting spool of the gas turbine engine.

Abstract: An insert is disposable between an exterior surface of an annular body and an annular flange and between a support wall supportive of the annular flange and surface features of the exterior surface. The insert includes a forward section sized to fit between and to extend along respective arc-segments of the exterior surface and the annular flange and an aft section. The forward section includes a first end wall abuttable with the support wall, a second end wall and inner and outer diameter surfaces that extend between the first and second end walls for abutment with the exterior surface and the annular flange, respectively. The aft section extends from the second end wall to be engageable with the surface features.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Abstract: A rotating component for a turbine engine includes a main component portion including a web and a platform located at a radially outboard portion of the web, relative to an axis of rotation of the rotating component. A snap surface is located at the platform and is configured to interlock the rotating component with an adjacent rotating component. A transition surface extends from the main component portion to the snap surface and includes two or more different radii.

Abstract: A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter operable to drive rotation of a starting spool of the gas turbine engine and a starter air valve operable to deliver compressed air to the air turbine starter in response to the starter air valve being open. The system also includes a metered orifice coupled in a bypass configuration around the starter air valve to deliver a reduced amount of the compressed air to the air turbine starter while the starter air valve is closed. The reduced amount of the compressed air delivered to the air turbine starter limits a motoring speed of the gas turbine engine below a resonance speed of the starting spool of the gas turbine engine.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Abstract: A rotating component for a turbine engine includes a main component portion including a web and a platform located at a radially outboard portion of the web, relative to an axis of rotation of the rotating component. A snap surface is located at the platform and is configured to interlock the rotating component with an adjacent rotating component. A transition surface extends from the main component portion to the snap surface and includes two or more different radii.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Abstract: A seal is positioned radially outwardly of a compressor blade. The seal has a seal hook facing in a downstream direction. A seal mount has a mount hook for receiving the seal hook in a gap. The hook face in an upstream direction. The seal mount has an upstream portion extending from an upstream end into the gap. The mount hook extends into a web which extends in a downstream direction. A thermal barrier coating on the upstream portion of the seal mount extends to a downstream end. There is a thermal barrier coating on a radially inner surface of the mount hook, and along the web to a downstream coating end. An upstream end of the coating on the inner surface of the hook being formed axially upstream of the downstream end of the coating on the upstream portion.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Abstract: A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained.

Abstract: A reinforced structural guide vane system includes an outer casing; a center body within the outer casing; a plurality of structural guide vanes extending between and connected to the center body and the outer casing; and a plurality of strut rods extended between and connected to the outer casing and to the center body.

Abstract: A split disk assembly for a gas turbine engine includes a forward disk section and an aft disk section, the aft disk section engageable with the forward disk section to retain a multitude of rotor blades therebetween.