Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and is driven by the input shaft. A component of the gear assembly drives the output shaft. The gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

Abstract: There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.

Abstract: There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.

Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.

Abstract: A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and is driven by the input shaft. A component of the gear assembly drives the output shaft. The gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.

Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.

Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.

Abstract: A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.

Abstract: A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation.

Abstract: A method facilitates balancing a gas turbine rotor. The method includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opposite the leading edge, and coupling a balance clip to the at least one turbine blade. The balance clip includes a first portion having a first length that enables the clip to extend between the tip shroud leading and trailing edges and includes a first hook that couples to the tip shroud leading edge, a shorter second portion that extends only partially from at least one of the tip shroud trailing and leading edges towards the opposite shroud edge, and a second hook that extends between the first and second portions and couples to at least one of the tip shroud leading and trailing edges.

Abstract: A method enables a gas turbine engine to be operated. The method comprises supplying cooling fluid into a manifold ring that includes a plurality of distribution ports defined by a sidewall connected by a radially inner wall, channeling the cooling fluid circumferentially through the manifold ring and through at least one distribution port that is defined by a wall that extends arcuately across at least one turbine nozzle, and discharging cooling fluid from the distribution ports radially inwardly towards the at least one turbine nozzle positioned radially inward from the manifold ring.

Abstract: A method for balancing a gas turbine rotor includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opposite the leading edge, and coupling a balance clip to the at least one turbine blade. The balance clip includes a first portion having a first length that enables the clip to extend between the tip shroud leading and trailing edges and includes a first hook that is configured to couple to the tip shroud leading edge, a second portion having a second length that is shorter than the first length, such that the second portion extends only partially from at least one of the tip shroud trailing and leading edges towards the opposite shroud edge, and a second hook that extends between the first and second portions and is configured to couple to at least one of the tip shroud leading and trailing edges.

Abstract: A turbine nozzle includes a hollow vane having opposite pressure and suction sides extending in span between outer and inner bands. The vane includes a forward flow channel behind the leading edge, an aft flow channel in front of the trailing edge, and a middle flow channel disposed therebetween. The three flow channels are disposed in flow communication with an outer plenum outside the outer band for receiving cooling air therefrom. The forward and middle channels are also disposed in flow communication with an inner plenum below the inner band for discharging the air. The aft channel discharges air through the inner band outside the inner plenum in split flow at different pressures.

Abstract: A method enables a gas turbine engine to be operated. The method comprises supplying cooling fluid into a manifold ring that includes a plurality of distribution ports defined by a sidewall connected by a radially inner wall, channeling the cooling fluid circumferentially through the manifold ring and through at least one distribution port that is defined by a wall that extends arcuately across at least one turbine nozzle, and discharging cooling fluid from the distribution ports radially inwardly towards the at least one turbine nozzle positioned radially inward from the manifold ring.