Abstract: A gas turbine engine includes a combustor and a valve coupled to the combustor. The valve includes a valve body, a valve stem, and an actuator. The valve body is formed to define an air chamber. The valve stem is movable between a closed position and an open position. The actuator is configured to move selectively the valve stem between the closed position and the open position.

Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight is located in a space radially between the first rotor and the second rotor.

Abstract: A gas turbine engine including an auxiliary compressor for pressuring cooling air delivered to turbine section components is disclosed. The auxiliary compressor is configured to increase the pressure of compressed air received from a primary compressor prior to movement of the compressed air to cooling air passageways of the turbine system.

Abstract: A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

Abstract: A valve includes a valve body, a valve stem, and an actuator. The valve body is formed to define an air chamber. The valve stem is movable between a closed position and an open position. The actuator is configured to move selectively the valve stem between the closed position and the open position.

Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight assembly is configured to balance a weight distribution of the rotor assembly.

Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight located in a space radially between the first rotor and the second rotor.

Abstract: A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

Abstract: A gas turbine engine system includes a gas turbine engine, an accessory gearbox, and a flywheel powered barring engine system. The gas turbine engine includes a rotor and a turbine. The accessory gearbox is connected with the rotor. The flywheel powered barring engine system is connected with the accessory gearbox and configured to rotate the rotor after shut down of the gas turbine engine.

Abstract: A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

Abstract: A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

Abstract: A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

Abstract: A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

Abstract: An anti-rotation device for a pair of threaded components includes a pair of ratchet interfaces and a spring element. A first ratchet interface and the spring element are movably disposed within a first threaded component, and a second ratchet interface is disposed at a mating end of a second threaded component. During relative rotation of the pair of threaded components, the ratchet interfaces engage, providing a resistance to the threaded components loosening that is greater than a resistance that the ratchet interfaces provide to the threaded components tightening. The anti-rotation device engages automatically upon relative rotation of the threaded components, and not as a separate step occurring after rotation. Additionally, the anti-rotation device may be especially useful in systems where various types of movement can cause the threaded components to loosen, and where visual access to the anti-rotation device is impeded.

Abstract: A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

Abstract: The present disclosure relates to a gas turbine engine including a turbine wheel mounted for rotation about a central axis and a turbine shroud ring mounted radially outward from the turbine wheel. The turbine wheel includes a plurality of blades that are spaced apart radially from the turbine shroud ring to establish a blade tip clearance gap. The gas turbine engine further includes a blade tip clearance control system that passively controls the size of the clearance gap based on engine operation.

Abstract: An anti-rotation device for a pair of threaded components includes a pair of ratchet interfaces and a spring element. A first ratchet interface and the spring element are movably disposed within a first threaded component, and a second ratchet interface is disposed at a mating end of a second threaded component. During relative rotation of the pair of threaded components, the ratchet interfaces engage, providing a resistance to the threaded components loosening that is greater than a resistance that the ratchet interfaces provide to the threaded components tightening. The anti-rotation device engages automatically upon relative rotation of the threaded components, and not as a separate step occurring after rotation. Additionally, the anti-rotation device may be especially useful in systems where various types of movement can cause the threaded components to loosen, and where visual access to the anti-rotation device is impeded.

Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along the engine case for a turbine of a gas turbine engine. The distribution manifold may include a passageway for a thermal fluid, an inlet configured to direct the thermal fluid into the passageway, an inner surface extending along and facing the outer surface of the engine case, and a plurality of outlets configured to direct the thermal fluid onto the outer surface of the engine case. The thermal fluid may include bypass air. A component may add kinetic energy to the thermal fluid.

Abstract: An axial flow compressor comprises a tubular casing which encases a rotatable shaft, a pair of rotor segments coupled to the rotatable shaft and each comprising a bladed disc, and a banded stator segment disposed between the pair of rotor segments and comprising a plurality of stator vanes extending between an outer flowpath ring and an inner flowpath ring. A method of assembling an axial flow compressor comprises installing a rotor segment inside a tubular compressor casing, installing a vane segment adjacent the installed rotor segment, and repeating the steps of installing a rotor segment and vane segment until a desired number of rotor segment and vane segment pairs are installed.

Abstract: A compressor shroud assembly in a turbine engine having a dynamically moveable shroud for encasing a rotor segment. The rotor segment comprises a bladed disc. The compressor shroud assembly maintains a clearance gap between the shroud and the blade tips of the bladed disc. The assembly comprises a static compressor casing, a shroud mounted to the casing, and an actuator mounted to the casing. The shroud comprises a flowpath boundary member spaced radially inward from the casing, the flowpath boundary member being moveable relative to the casing in a radial direction. The actuator is coupled to the shroud for effecting the movement of the flowpath boundary member.