A gas turbine engine (100) includes a core engine casing (114), a bypass duct (122) and a core engine duct (111). The gas turbine engine (100) further includes a plurality of flaps (130) pivotally coupled to the core engine casing (114) and arranged circum...

A heat exchanger apparatus (54,82) including at least one cooling channel (76,84) formed within and about an engine booster lip (74) or an engine nacelle and configured to receive a flow of a circulating working fluid; and at least one fluid port (90) comm...

A gas turbine engine has a compressor section with rotational compressor components rotatable with respect to static compressor components. A compressed air bleed arrangement is provided to cool one or more other rotational components of the gas turbine en...

A gas turbine engine includes a compressor powered by a turbine (24). The turbine (24) includes a nozzle (34) having vanes (42) extending between outer and inner bands (44,46). Each vane (42) includes an internal cooling plenum (48) and a bypass tube (50) ...

A gas turbine engine (10) includes a first fire zone (Zone 3) in the region of a core of the engine and a second fire zone (Zone 1) in the region of a fan case of the engine, the first and second fire zones being separated by fire walls. The first fire zon...

The present invention relates to a bleed deflector for a gas turbine engine. The bleed deflector 20 comprises an inlet portion 22 for receiving bleed air from the engine, a perforated top plate 44 for discharging the bleed air into a duct 30, and an aerody...