A generator is installed on and provides electrical power from a turbine by converting the turbine's mechanical energy to electricity. The generated electrical power is used to power controls of the turbine so that the turbine can remain in use through its own energy. The turbine can be a safety-related turbine in a nuclear power plant, such that, through the generator, loss of plant power will not result in loss of use of the turbine and safety-related functions powered by the same. Appropriate circuitry and electrical connections condition the generator to work in tandem with any other power sources present, while providing electrical power with properties required to safely power the controls.

A system for delivering a flow stream of a gas to a compressor. A shroud extends from an inlet to the compressor and defines a main inlet passage configured to direct the flow stream from the inlet to the compressor. A communication plenum is separated from the main inlet passage. A port system includes first and second port subsystems that each provide an opening between the main inlet passage and the communication plenum. The first port subsystem is disposed further from the compressor than the second port subsystem. The port system is configured so that a portion of the gas enters or exits the compressor through the second port subsystem, depending on operating conditions of the compressor.

A system for delivering a flow stream of a gas to a compressor. A shroud extends from an inlet to the compressor and defines a main inlet passage configured to direct the flow stream from the inlet to the compressor. A communication plenum is separated from the main inlet passage. A port system includes first and second port subsystems that each provide an opening between the main inlet passage and the communication plenum. The first port subsystem is disposed further from the compressor than the second port subsystem. The port system is configured so that a portion of the gas enters or exits the compressor through the second port subsystem, depending on operating conditions of the compressor.

Heat exchanger assemblies including turning vanes are taught herein. In preferred embodiments, the heat exchanger assembly comprises: an inlet duct; a heat exchanger coupled to the inlet duct and a plurality of turning vanes coupled to the heat exchanger and protruding into the inlet duct. The intake plane of the heat exchanger is at an angle between 0 degrees and 90 degrees to the primary flow direction of the inlet duct. The plurality of turning vanes comprise: a straight leading edge of length L that is parallel to the primary flow direction of the inlet duct; a convex lower surface that transitions a bottom of the leading edge to an upper wall of a lower channel of the heat exchanger; and a concave upper surface that transitions a distal point of the turning vane to a second channel of the heat exchanger.

Heat exchanger assemblies including turning vanes are taught herein. In preferred embodiments, the heat exchanger assembly comprises: an inlet duct; a heat exchanger coupled to the inlet duct and a plurality of turning vanes coupled to the heat exchanger and protruding into the inlet duct. The intake plane of the heat exchanger is at an angle between 0 degrees and 90 degrees to the primary flow direction of the inlet duct. The plurality of turning vanes comprise: a straight leading edge of length L that is parallel to the primary flow direction of the inlet duct; a convex lower surface that transitions a bottom of the leading edge to an upper wall of a lower channel of the heat exchanger; and a concave upper surface that transitions a distal point of the turning vane to a second channel of the heat exchanger.

A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.

A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.

A system for delivering a flow stream of a gas to a compressor. A shroud extends from an inlet to the compressor and defines a main inlet passage configured to direct the flow stream from the inlet to the compressor. A communication plenum is separated from the main inlet passage. A port system includes first and second port subsystems that each provide an opening between the main inlet passage and the communication plenum. The first port subsystem is disposed further from the compressor than the second port subsystem. The port system is configured so that a portion of the gas enters or exits the compressor through the second port subsystem, depending on operating conditions of the compressor.

A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.