Abstract: A thermal management system for a component of a gas turbine engine is disclosed. In various embodiments, the thermal management system includes a manifold extending circumferentially about a longitudinal axis and defining a plenum; a cooling fluid transfer tube disposed within the plenum and configured to transfer a component cooling fluid from a component cooling fluid source to the component; and a cooling fluid passageway connected to the manifold and configured to transfer a plenum cooling fluid from a plenum cooling fluid source to the plenum.

Abstract: A vane strut positioning and securement system includes a housing including a washer aperture defined in an inner diameter thereof and a lock washer disposed within the washer aperture of the housing, the lock washer configured to lock a vane strut orientation under compression against a vane strut washer. The washer aperture is defined partially through a thickness of the housing, and the housing includes a strut post opening defined through the housing from the inner diameter to an outer diameter of the housing.

Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.

Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.

Abstract: A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.

Abstract: A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.

Abstract: A gas turbine engine includes a bearing support ring with a first annular body and a second annular body disposed radially inward of the first annular body. A radial spring is connected to the first annular body and the second annular body. The gas turbine engine includes a frame with a case that extends around the first annular body. The frame includes an annular member connected to the case and positioned radially between the radial spring and the second annular body. A fluid port extends radially through the annular member. A seal is disposed around the annular member and forward of the fluid port. A first fluid passage extends through the case. A second fluid passage is formed between the bearing support ring and the frame and extends from the first fluid passage to the fluid port. A bearing outer race is disposed inward of the second annular body.

Abstract: An auxiliary compressor for a gas turbine engine is disclosed. The auxiliary compressor includes a first axial rotor, a second axial rotor positioned downstream of the first axial rotor, and a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.

Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.

Abstract: A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.

Abstract: An auxiliary compressor for a gas turbine engine is disclosed. The auxiliary compressor includes a first axial rotor, a second axial rotor positioned downstream of the first axial rotor, and a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.

Abstract: A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.

Abstract: A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.

Abstract: Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path.

Abstract: A bearing system for a gas turbine engine includes an outer housing and a first ball bearing assembly disposed radially inward from the outer housing relative a center axis of the outer housing. The bearing system also includes a second ball bearing assembly disposed radially inward from the outer housing and positioned axially aft of the first ball bearing assembly. The bearing system also includes a resilient member that is connected to the outer housing and compressed against at least one of a first outer race of the first ball bearing assembly and a second outer race of the second ball bearing assembly in an axial direction parallel to the center axis.

Abstract: A gas turbine engine includes a bearing support ring with a first annular body and a second annular body disposed radially inward of the first annular body. A radial spring is connected to the first annular body and the second annular body. The gas turbine engine includes a frame with a case that extends around the first annular body. The frame includes an annular member connected to the case and positioned radially between the radial spring and the second annular body. A fluid port extends radially through the annular member. A seal is disposed around the annular member and forward of the fluid port. A first fluid passage extends through the case. A second fluid passage is formed between the bearing support ring and the frame and extends from the first fluid passage to the fluid port. A bearing outer race is disposed inward of the second annular body.

Abstract: A baffle within a gas turbine engine includes a cylindrical flange with a multiple of holes at least partially therearound.

Abstract: A bearing system for a gas turbine engine includes an outer housing and a first ball bearing assembly disposed radially inward from the outer housing relative a center axis of the outer housing. The bearing system also includes a second ball bearing assembly disposed radially inward from the outer housing and positioned axially aft of the first ball bearing assembly. The bearing system also includes a resilient member that is connected to the outer housing and compressed against at least one of a first outer race of the first ball bearing assembly and a second outer race of the second ball bearing assembly in an axial direction parallel to the center axis.

Abstract: A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.

Abstract: A method for distributing liquid in a gas turbine engine is disclosed. The method includes rotating a fan shaft coupled to a spool via a fan drive gear system. The spool drives rotation of the fan shaft through the fan drive gear system during operation of the gas turbine engine. A pump is driven via the fan shaft. Liquid is supplied from a sump to the pump under a first operating condition. Liquid is supplied from an auxiliary reservoir to the pump under a second operating condition. Liquid is pumped to a damper.