A bleed system including control circuitry and a variable jet pump. The control circuitry is configured to receive a signal indicative of a fluid parameter in the bleed system and cause the jet pump to alter a mixing ratio of a higher pressure gas and a lower pressure gas based on the signal. The jet pump is configured to combine the lower pressure gas and the higher pressure gas in the mixing ratio to generate a mixed gas. The jet pump is configured to supply the mixed gas to one or more gas loads in the bleed system. In examples, the control circuitry is configured to establish a system setpoint for the fluid parameter based on an operating status of the one or more gas loads.

An eductor for an auxiliary power unit with a gas turbine engine and a load compressor incorporates an eductor housing having an cooling airflow inlet and a turbine exhaust inlet opening fluidly connected through a primary plenum to an outlet opening. A splitter plate is positioned in the primary plenum fixing a flow stagnation point with respect to a wall of the primary plenum.

An eductor for an auxiliary power unit with a gas turbine engine and a load compressor incorporates an eductor housing having an cooling airflow inlet and a turbine exhaust inlet opening fluidly connected through a primary plenum to an outlet opening. A splitter plate is positioned in the primary plenum fixing a flow stagnation point with respect to a wall of the primary plenum.

A turbine exhaust drain system has a sump where liquid collects and a suction pipe having an inlet end fluidly connected to the sump and an outlet end fluidly connected to a core gas path of a turbine exhaust case. In use, the combustion gases flowing through the exhaust case creates a venturi effect to draw the liquid from the sump into the core gas path where the liquid and the combustions gases combine into a mixed flow before being discharged through an outlet end of the exhaust case.

A fluid supercharging device (3, 5), comprising: a rotating shaft (7); a vane disc (308) coaxially fixed to the rotating shaft (7); a plurality of fan blades (301) fixed around a perimeter of the vane disc (308); the back side of the fan blades 301 being provided with at least one fluid guiding inlet (305), an end of the back side distal from the vane disc (308) is provided with a fluid guiding outlet (306, 307), a fluid channel (304) communicating the fluid guiding inlet (305) with the fluid guiding outlet (306, 307) is provided along a lengthwise direction inside the fan blades; the fan blades (301) rotate to generate a centrifugal force such that a fluid flows into the fluid channel via the fluid guiding inlet on the back side, and flows out of the fluid guiding outlet along the lengthwise direction of the fan blades.

A fluid supercharging device (3, 5), comprising: a rotating shaft (7); a vane disc (308) coaxially fixed to the rotating shaft (7); a plurality of fan blades (301) fixed around a perimeter of the vane disc (308); the back side of the fan blades 301 being provided with at least one fluid guiding inlet (305), an end of the back side distal from the vane disc (308) is provided with a fluid guiding outlet (306, 307), a fluid channel (304) communicating the fluid guiding inlet (305) with the fluid guiding outlet (306, 307) is provided along a lengthwise direction inside the fan blades; the fan blades (301) rotate to generate a centrifugal force such that a fluid flows into the fluid channel via the fluid guiding inlet on the back side, and flows out of the fluid guiding outlet along the lengthwise direction of the fan blades.

A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath, a turbine section fluidly connected to the combustor via the primary flowpath, and a plurality of fuel injectors disposed within the combustor. The plurality of fuel injectors including at least one start fuel injector. Also included is a controller having a memory and processor. The memory stores instructions configured to cause the at least one start fuel injector to pulse fuel through the start injector nozzle, thereby preventing stagnant fuel in the start injector nozzle from exceed a coking temperature threshold.

A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath, a turbine section fluidly connected to the combustor via the primary flowpath, and a plurality of fuel injectors disposed within the combustor. The plurality of fuel injectors including at least one start fuel injector. Also included is a controller having a memory and processor. The memory stores instructions configured to cause the at least one start fuel injector to pulse fuel through the start injector nozzle, thereby preventing stagnant fuel in the start injector nozzle from exceed a coking temperature threshold.

The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.

The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.