An air turbine start system is provided that includes an air turbine starter, a starter air valve, a turbine speed sensor, and a circuit. The starter air valve is movable between an open position, in which the pressurized air may flow into the air turbine starter, and a closed position, in which pressurized air does not flow into the air turbine starter. The turbine speed sensor is coupled to the air turbine starter, and is configured to sense the rotational speed of the turbine and supply a rotational speed signal representative thereof. The circuit is coupled to receive the rotational speed signal and is configured, upon receipt thereof, to determine whether the starter air valve is in the closed position or an open position.

A valve includes a housing with a mounting portion, a venting portion, and a cap portion. The valve also includes a piston in the housing with a shaft, a disc, and a flange, the piston being moveable between a closed position and an open position. The valve also includes a vessel that is in contact with the cap portion and the flange wherein fluid pressure contained in the vessel biases the piston into one of the opened position and the closed position.

An apparatus for use in a gas turbine engine is disclosed comprising a bleed valve and an intermediate valve. In use the bleed valve is exposed to a source of pressurised air, and the bleed valve is movable between an open position, in which the bleed valve permits a flow of the pressurised air through the bleed valve and a closed position, in which the bleed valve does not permit a flow of the pressurised air through the bleed valve. The intermediate valve is operatively connected to the bleed valve and configured to selectively open and close the bleed valve, wherein the intermediate valve is configured in a mode of operation to close the bleed valve based on the pressurised air within the bleed valve exceeding a predetermined threshold.

A solenoid for a bleed valve includes a solenoid body with an actuation fluid passage, a bleed valve passage, and a drive fluid chamber. A main armature is disposed within the solenoid body and is movable between open and closed positions, the actuation fluid passage being in fluid communication with the control outlet in the open position, the actuation fluid passage being fluidly isolated from the bleed valve passage in the second position. A pilot armature is disposed within the solenoid body, is movable relative to the main armature, and is operably coupled to the main armature by the drive fluid chamber to move the main armature between the open and closed positions by controlling issue of a drive fluid into and out of the drive fluid chamber.

An actuator operable to drive a thrust reverser in a gas turbine engine, wherein the thrust reverser comprises first and second translatable sleeves. The actuator comprises a first actuating member moveable so as to translate the first sleeve and a second actuating member moveable so as to translate the second sleeve. The actuator further comprises an interlock arrangement operable in a locked mode in which the first actuating member and second actuating member are locked so as to move together and in an unlocked mode in which at least one of the first actuating member and second actuator member is free to move independently of the other. Operation of the actuator to open or close the thrust reverser comprises a first mode wherein the interlock arrangement is in the locked mode and a second mode wherein the interlock arrangement is in the unlocked mode.

A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.

A system includes a fluid distribution system. The fluid distribution system includes a first water wash nozzle configured to spray a wash fluid into an intake flow received through a bell mouth of a compressor during operation of the compressor in a water wash mode. The first water wash nozzle includes a first inlet end coupled to the bell mouth of the compressor, a first tip disposed opposite the first inlet end, and a first body of the first water wash nozzle extending from the first inlet end to the first tip toward an axis of the compressor. The first water was nozzle further includes a first outlet disposed at the first tip and configured to spray a first portion of the wash fluid into the intake flow during operation of the compressor in the water wash mode and a second outlet disposed along the first body and configured to spray a second portion of the wash fluid into the intake flow during operation of the compressor in the water wash mode.

A bleed valve includes a housing with an inlet coupled to an outlet by a duct, a guide tube with an orifice fixed in the housing between the inlet and the outlet, a piston, and baffle. The piston is slideably supported on the guide tube and is movable between an open and a closed position, the duct fluidly coupling the inlet and outlet in the open position, the duct fluidly separating the inlet and outlet in the closed position. The orifice fluidly couples the inlet and outlet in the open and closed positions to move piston between the open and closed positions according to differential pressure between the bleed valve inlet and outlet. The baffle is slideably supported by the guide tube to set the differential pressure at which the piston moves between the open and closed positions. Gas turbines and differential pressure adjustment methods are also described.

A gas turbine engine comprising: a duct extending about an axis, the duct including an outer-duct wall having an interior-duct surface circumscribing an interior of the duct and an exterior-duct surface radially outward of the interior-duct surface relative to the axis, the outer-duct wall defining an offtake opening extending from the interior-duct surface to the exterior-duct surface, the offtake opening in fluid communication between an offtake location inside the duct and outside the duct, and a bleed air offtake assembly including: an air line in fluid communication with inside the duct via the offtake opening, the air line having a first-line end defining a line inlet proximate to the outer-duct wall and a second-line end spaced from the first-line end; a valve located outside the duct and fluidly connected to the air line via the second-line end, and a conduit having a conduit inlet in fluid communication with inside the air line at a resonance location between the first-line end and the second-line end upstream of the valve, and a conduit outlet in fluid communication with inside the duct at a relief location spaced from the offtake location.

A hydraulic and pneumatic control circuit for a turbojet, a main hydraulic line having an oil/fuel heat exchanger with a function of transferring heat from the oil flowing in an oil circuit of the turbojet to the fuel flowing in the main hydraulic line, the circuit having a first hydraulic line for feeding fuel to a combustion chamber of the turbojet, a second hydraulic line for feeding fuel to one or more actuators for controlling variable geometry equipment, each actuator being fed with fuel via an electrohydraulic servovalve, a pneumatic line for feeding air to a pneumatic control member for bleed valves of a compressor and a blade tip clearance control valve of a turbine of the turbojet, and a fuel/air heat exchanger positioned on the second hydraulic line upstream from the hydraulic servovalve and on the pneumatic line upstream from the pneumatic control member.