An apparatus for an aircraft propulsion system includes a variable area nozzle apparatus (66). The variable area nozzle apparatus (66) includes a plurality of panels (76), a plurality of inter-panel members (78) and an actuation system (74). The panels (76...

In order to avoid disturbing noises in a flap device (10), in particular a wastegate flap, in an exhaust turbocharger arrangement, a stop (28) for the flap device (10) is formed in a turbine housing (2) in which the controllable flap device (10) is arrange...

A system (100) for controlling a flow rate of a compressed cooling medium between a compressor section (12) and a turbine section (16) of a gas turbine (100) includes a flow path (102) that is defined between the compressor section and the turbine section ...

A variable area fan nozzles (14) comprising an array of rigid petals (18) hinged to a lip area at the downstream end of a thrust reverser sleeve (or half-sleeve). In one embodiment, the actuation system comprises a rotatable ring segment (28), a drive syst...

A compressor (110) of a gas turbine system comprises a fluid flow control device (220) and an impingement angle control device (230) downstream of the fluid flow control device. The fluid flow control device (220) controls a fluid flow rate of fluid enteri...

An assembly can include a valve seat (530) for an exhaust bypass valve (500) of a serial turbocharger system where the valve seat includes a base portion and a wall portion that extends axially away from the base portion; and a gasket (540) that includes a...

A gas path flow blocker comprising a plurality of vanes (21) each comprising a forward portion (25) and an aft portion (23) defining a plurality of gas paths, a forward ring (15) comprising a central axis (19) about which is circumferentially disposed the ...

A axial flow rotary machine (10) comprises a primary flow path (16) for a working medium, a secondary flow path (18) for the working medium, a bleed system (20) for allowing a bleed portion of the working medium flowing in the primary flow path (16) to be ...

A valve assembly 200 for supplying cooling air to a nozzle 113 of a gas turbine engine 100. The nozzle 113 can move between a first configuration and a second configuration. The valve assembly 200 includes a first member 215 having openings 217 that receiv...