An aircraft turbomachine module comprising a ventilation device configured to have a cooling air flow circulate in the turbomachine module, the ventilation device comprising an air outlet, blocking means fixed to the air outlet and mobile between a blocking position of the air outlet and an opening position of the air outlet, and locking means configured to maintain the blocking means in one of the blocking position and the opening position when the temperature within the module is less than a predetermined threshold value, the blocking means being configured to adopt the other of the blocking position and the opening position when the temperature within the module is greater than said predetermined threshold value.

A bleed valve assembly of a gas turbine engine includes two or more valve segments extending circumferentially around a central longitudinal axis of the gas turbine engine, and a first splice bracket spanning a first joint between a first valve segment and a second valve segment of the two or more valve segments. The first splice is bracket secured to the first valve segment and the second valve segment. A second splice bracket spans a second joint between the first valve segment and the second valve segment. The second splice bracket is secured to the first valve segment and the second valve segment.

A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.

This invention relates to a turbocharger (210). More specifically, the invention relates to an axial-entry type turbocharger, where the exhaust gases are directed to meet the turbine wheel at least front-on, having a variable volume for controlling pressure, allowing for a substantially uniform pressure and uniform velocity to act simultaneously on and around the turbine wheel, while enabling the volume of the turbocharger to be adjusted under predetermined set pressure conditions. The turbocharge includes: a turbine housing defining a substantially axial primary flow duct, a primary turbine wheel (216) mounted along such primary flow duct (214), and a diverter (218) for diverting flow passing thereover into a primary annular flow path directed to impinge the primary turbine wheel (216). The turbine housing of the turbocharger defines a secondary flow duct (222) for directing some flow to: (i) impinge the primary turbine wheel (216); and/or (ii) bypass the primary turbine wheel (216). A secondary flow duct gate (223) controls flow through the secondary flow duct (222) and is movable between a closed position, wherein under low pressure conditions flow is restricted from flowing through the secondary flow duct (222), and an open position, wherein flow though the secondary flow duct (222) is enabled such that operative flow passes through both the primary and the secondary flow ducts (216, 222) under high pressure conditions. The turbocharger further includes at least one compressor coupled to the primary turbine wheel (216) via a primary transmission thereby to transmit drive from the primary turbine wheel (216) to the compressor.

A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.

Controller for controlling a bleed valve including a first body with an internal cavity connected to an air inlet port and an air outlet port, a second body including a chamber, a mobile member in the cavity and in the chamber, connecting the two bodies. The member is mobile between a position whereby the ports fluidly communicate and a position whereby the ports are isolated, the member further including two pistons housed in the chamber and defining in this chamber at least two spaces. The controller also includes a fluid supply for at least one of the spaces for the purpose of moving the pistons in the chamber.

The invention relates to a compressor, in particular a gas compressor, for instance for a turbocharger, for compressing a gaseous fluid, having a compressor housing (40) in which a compressor wheel (41) is rotatably arranged, wherein the compressor housing (40) has a gas intake manifold (43), via which gas can be fed to the compressor wheel (41), a compressor duct (42) being provided, via which the compressed gas can be discharged from the compressor wheel (41), an adjustment device (60) being arranged in the area of the gas intake manifold (43), wherein the adjustment device (60) has orifice elements (70), which can be adjusted linearly between a closed position and an open position, and by means of which the opening cross-section of the gas intake manifold (43) in a duct area can be varied in order to form a minimum opening cross-section (Ömin) in the closed position and a maximum opening cross-section (Ömax) in the open position, wherein in each case two adjacent orifice elements (70) have sealing segments (73.1, 76.1) which, in the closed position, face each other, in particular rest against each other. To be able to reduce the noise emissions in such a compressor in a simple and effective manner, provision is made according to the invention that the orifice elements (70) can be adjusted into a retracted operating position, in which body areas of the orifice elements (70) at least in some areas delimit a recess, in particular a circumferential groove, in the gas intake manifold (43) to form a resonator, in particular a Helmholtz resonator, and wherein provision may in particular be made that the orifice elements (70) can be adjusted, preferably continuously, between several retracted operating positions.

A turbine vane assembly and a gas turbine including the turbine vane assembly are capable of adjusting a flow rate and a supply pressure of seal air by adjusting the area of a purge hole. The turbine vane assembly includes a turbine vane disposed between an outer platform and an inner platform; a U-ring unit formed of opposite sides that face each other and are each coupled to the inner platform to form a cavity; a first purge hole formed in one side of the U-ring unit to communicate with each of the cavity and a first wheel space, the first purge hole having an area that is adjustable in size; and a second purge hole formed in the other sides of the U-ring unit to communicate with each of the cavity and a second wheel space, the second purge hole having an area that is adjustable in size.

An auxiliary power unit (APU) control system for an aircraft is disclosed and includes an APU, an air inlet having an effective area, an air inlet door moveable to vary the effective area of the air inlet, an actuator configured to move the air inlet door into a set position, one or more processors, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the APU control system to receive one or more ambient signals indicative of an air density value. The system also determines the effective area of the air inlet based on the air density value. The system is further caused to instruct the actuator to move the air inlet door into the set position.

A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.