Abstract: An aspirating face seal assembly includes a stationary component and a seal body defining a seal face. The seal body defines a fluid feed passage within the seal body. The fluid feed passage includes an inlet, and one or more feed ports defined along the seal face. The seal body is moveably coupled to the stationary component via a resilient member. A first-pressure plenum is defined radially outward from the seal body and a second-pressure plenum is defined radially inward from the seal body. The seal assembly further includes a plenum seal forming a seal between a portion of the seal body and the stationary component and at least partially defining a third-pressure plenum in fluid communication with a high-pressure fluid source and with the inlet of the fluid feed passage. The third-pressure plenum is pressurized at a higher pressure than both the first-pressure plenum and the second-pressure plenum.

Abstract: Film riding dampers for rotating components are disclosed herein. An example damper assembly for a rotor includes a body including a first surface to form a first thin-film interface with the rotor, and a second surface to form an interface with a stator, and a damper rigidly coupled to the body including a casing including a damping medium and a plunger within the casing.

Abstract: Methods and apparatus to reduce vibration of a radial seal in a gas turbine engine are disclosed. An example apparatus includes a seal segment of a radial seal positioned between a rotor and a stator of a gas turbine engine, the seal segment including a first seal body adjacent the rotor and a first surface of the stator, a second seal body adjacent a second surface of the stator, the second surface opposite the first surface, the second seal body pivotable relative to the first seal body, and a pivot bar extending between the first seal body and the second seal body, and a damper operatively coupled to the pivot bar.

Abstract: A gas turbine engine includes a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator. A seal assembly defines a primary seal at an interface of the rotor and the stator and separates an inlet plenum from an outlet plenum. The seal assembly includes one or more aspiration conduits fluidly connected to the primary seal. One or more flingers are positioned at least partially between the seal assembly and the inlet plenum that define one or more passageways fluidly connecting the inlet plenum to the one or more aspiration conduits. The flingers are positioned to direct at least a portion of an airflow within the inlet plenum away from the one or more passageways.

Abstract: A turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. The shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. The at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.

Abstract: A gas turbine engine is provided. The gas turbine engine includes: a compressor section; a combustion section comprising an inner combustor casing defining in part an aft cavity with the compressor section and defining in part a diffuser cavity with an outer combustor casing; and a cooling system having: a compressor discharge pressure duct located outward of the outer combustor casing and positioned in fluid communication with the diffuser cavity, the compressor section, or both for receiving an airflow from the diffuser cavity, from the compressor section, or both; a heat exchanger in thermal communication with the compressor discharge pressure duct for reducing a temperature of the airflow; a cooling duct located inward of the outer combustor casing and in fluid communication with the compressor discharge pressure duct and the aft cavity for receiving the airflow and providing at least a portion of the airflow to the aft cavity.

Abstract: A seal assembly for a gas turbine includes a seal case, and a seal shoe arranged within the seal case. The seal shoe includes a main seal portion that is configured to engage with a radial bearing engagement portion of a rotor shaft, a radial bearing surface that engages with the radial bearing engagement portion of the rotor shaft, at least one hydrodynamic lift cavity extending through the radial bearing surface, and at least one airflow passage extending from a first side of the seal shoe through the at least one hydrodynamic lift cavity and providing airflow communication between the first side of the seal shoe and the at least one hydrodynamic lift cavity.

Abstract: A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. The rotary machine also includes a seal assembly at the rotor-stator interface. The seal assembly includes a seal rotor, a seal stator, a seal slider, and a seal defined by a rotor face of the seal rotor and a slider face of the seal slider. Further, the seal assembly includes a flexible joint connected between the slider face and a primary seal body of the seal slider. The flexible joint is configured to locally decouple movement of the slider face from the seal slider to allow the slider face to track movement of the rotor apart from the primary seal body.

Abstract: A gas turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement to define a diffuser cavity between the compressor section and the combustor section, and an aft cavity. A compressor discharge pressure duct fluidly draws air from the diffuser cavity, passes it through a heat exchanger to cool the air, and then supplies the cooled air to the aft cavity.

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Abstract: A seal assembly for a gas turbine includes a seal case, and a seal shoe arranged within the seal case. The seal shoe includes a main seal portion that is configured to engage with a radial bearing engagement portion of a rotor shaft, a radial bearing surface that engages with the radial bearing engagement portion of the rotor shaft, at least one hydrodynamic lift cavity extending through the radial bearing surface, and at least one airflow passage extending from a first side of the seal shoe through the at least one hydrodynamic lift cavity and providing airflow communication between the first side of the seal shoe and the at least one hydrodynamic lift cavity.

Abstract: A turbine engine is provided. The turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a first seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprising a prestressed spring assembly extending from the seal segment for biasing the seal segment along the radial direction.

Abstract: A seal assembly for a gas turbine includes a seal case, and a seal shoe arranged within the seal case. The seal shoe includes a main seal portion that is configured to engage with a radial bearing engagement portion of a rotor shaft, a radial bearing surface that engages with the radial bearing engagement portion of the rotor shaft, at least one hydrodynamic lift cavity extending through the radial bearing surface, and at least one airflow passage extending from a first side of the seal shoe through the at least one hydrodynamic lift cavity and providing airflow communication between the first side of the seal shoe and the at least one hydrodynamic lift cavity.

Abstract: A rotary machine, such as a turbomachine of a gas turbine engine, for example, including a rotor and a rotor seal assembly. The rotor is rotatable about a rotational axis and has a rotor seal face. The rotor seal assembly includes a seal body, one or more primary fluid conduits formed in the seal body, and a retraction assembly. The seal body has a seal face and is positionable to form a fluid-bearing gap between the seal face of the seal body and the rotor seal face. The one or more primary fluid conduits are fluidly connected to the fluid-bearing gap to supply a fluid to the fluid-bearing gap. The retraction assembly is connected to the seal body to move the seal body in a retraction direction away from the rotor seal face.

Abstract: A torque extraction system for a turbine engine includes an electric machine coupled to a shaft of the turbine engine by way of a gearbox disposed between the electric machine and the shaft of the turbine engine, and the electric machine draws torque from the shaft and converts the torque to electrical energy. A power bus is electrically coupled to the electric machine and provides power to the electric machine. A sensor senses vibrational forces acting on a rotor of the turbine engine, and a controller electrically coupled to the electric machine receives signals from the sensor corresponding to the sensed vibrational forces. The controller operates the gearbox disposed between the electric machine and the shaft of the turbine engine to increase the torque that the electric machine draws from the shaft when the vibrational forces sensed by the sensor meet or exceed a predetermined threshold.

Abstract: A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.

Abstract: A turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. The shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. The at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.

Abstract: A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Abstract: A turbine engine is provided. The turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a first seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprising a prestressed spring assembly extending from the seal segment for biasing the seal segment along the radial direction.