Abstract: A gas turbine engine including a core having a compressor section fluidly connected to a combustor via a primary flowpath and a turbine section connected to the combustor via the core flow path. An assembly is disposed within the gas turbine engine and includes a first part connected to a second part via a radial stack joint. The first part includes a radially inward facing surface contacting a corresponding radially outward facing surface of the second part. A fastener protrudes through the first part and the second part and is configured to maintain the relative positions of the first part and the second part. A channel is disposed on at least one of the radially inward facing surfaces and is positioned between the fastener and a circumferential edge of the first part. The channel is connected to at least one cooling air source.

Abstract: A gas turbine engine including a core having a compressor section fluidly connected to a combustor via a primary flowpath and a turbine section connected to the combustor via the core flow path. An assembly is disposed within the gas turbine engine and includes a first part connected to a second part via a radial stack joint. The first part includes a radially inward facing surface contacting a corresponding radially outward facing surface of the second part. A fastener protrudes through the first part and the second part and is configured to maintain the relative positions of the first part and the second part. A channel is disposed on at least one of the radially inward facing surfaces and is positioned between the fastener and a circumferential edge of the first part. The channel is connected to at least one cooling air source.

Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.

Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a first O-ring disposed between the annular ring and the fluid transfer tube, a second O-ring disposed between the base member and the annular ring, and an attachment ring configured to secure the annular ring and the base member to the casing.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, a housing configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a bellows surrounding the fluid transfer tube and positioned between the housing and the casing, and a wear ring disposed between the housing and the bellows.

Abstract: A cover assembly is disclosed. In various embodiments, the cover assembly includes a cover configured to close a passageway through a casing, the cover having a first keyhole slot; and a first captive fastener configured to extend through the first keyhole slot and into the casing.

Abstract: An airflow deflector is provided that includes at least one liner attachment flange, a deflector panel, and at least one deflector leg. The at least one liner attachment flange has a liner side surface and an opposing outer surface. The at least one deflector leg extends between and is attached to the at least one liner attachment flange. The at least one deflector leg extends a distance between the deflector panel and the liner attachment flange to maintain the deflector panel a separation distance from the liner attachment flange. The airflow deflector is configured for insertion of the at least one deflector leg and the deflector panel within a liner aperture.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, a housing configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a bellows surrounding the fluid transfer tube and positioned between the housing and the casing, and a wear ring disposed between the housing and the bellows.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a first O-ring disposed between the annular ring and the fluid transfer tube, a second O-ring disposed between the base member and the annular ring, and an attachment ring configured to secure the annular ring and the base member to the casing.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a boot seal configured to surround a length of the fluid transfer tube, the boot seal having a first end and a second end and a seal ring disposed at the first end, an attachment ring configured to mate with the seal ring and to secure the seal ring against a casing, an annular ring configured to mate with an interior surface of the boot seal at the second end and to surround a portion of the fluid transfer tube, and a clamp ring configured to surround the second end of the boot seal proximate the annular ring.

Abstract: An airflow deflector is provided that includes at least one liner attachment flange, a deflector panel, and at least one deflector leg. The at least one liner attachment flange has a liner side surface and an opposing outer surface. The at least one deflector leg extends between and is attached to the at least one liner attachment flange. The at least one deflector leg extends a distance between the deflector panel and the liner attachment flange to maintain the deflector panel a separation distance from the liner attachment flange. The airflow deflector is configured for insertion of the at least one deflector leg and the deflector panel within a liner aperture.