About 34 results
https://drivepatents.com/patents/988658 · 17 Jul 2013
A method for recovering air in an aircraft includes bleeding bypass air (122;196) from an engine bypass (76;152), bleeding core air (120;194) from an engine core (74;150), and placing the bypass air and the core air in a heat exchange relationship to produ...
https://drivepatents.com/patents/988877 · 10 Jul 2013
A gas turbine (10) includes a compressor (12), a combustor (14) downstream from the compressor (12) and a heat transfer system (30), wherein the heat transfer system (30) receives a compressed working fluid (22) from the compressor (12). A fluid coupling (...
https://drivepatents.com/patents/990231 · 29 May 2013
The method involves supplying low calorific fuel and medium calorific fuel e.g. synthesis gas to a gas turbine (10). The gas turbine is provided with a secondary-air system with two cool air stages (44d,44c) to perform refrigeration of turbine components. ...
https://drivepatents.com/patents/984968 · 24 Apr 2013
A gas turbine engine includes a first pump (86) driven by a spool (30), an air-oil cooler (88) downstream of the first pump (86), a second pump (90) driven by the spool (30) and an air-air precooler (92) downstream of the second pump (90). The air-air prec...
https://drivepatents.com/patents/984949 · 24 Apr 2013
A gas turbine engine (20) includes a constant speed transmission (110) driven by a spool (30). The transmission may drive first and second pumps (86, 90) of a Thermal Management System (82) and an Environmental Control System (84).
https://drivepatents.com/patents/985380 · 27 Mar 2013
A bleed air duct joint insulation means (204) is disclosed in which a leak vent (205) comprises valve means (303).
STRUCTURE FOR EXTRACTING COMPRESSED AIR FROM COMPRESSOR OF GAS TURBINE ENGINE AND GAS TURBINE ENGINE
https://drivepatents.com/patents/992386 · 20 Mar 2013
Provided is a structure of a gas turbine engine for extracting a part of compressed air generated by a compressor. The structure comprises a cylindrical housing 13 extending around an axis C and forming therein at least a part of a compressing chamber in w...
https://drivepatents.com/patents/994363 · 2 Jan 2013
A gas turbine inlet heating system (2) is disclosed. In one embodiment, the system (2) includes: a compressor (4) including: an inlet bellmouth (6) adjacent to a set of inlet guide vanes (IGVs) (8); and an outlet (10) fluidly connected to the inlet bellmou...
https://drivepatents.com/patents/995654 · 28 Nov 2012
A bleed assembly of a gas turbine engine comprises a bleed flow discharge device (136) adapted to discharge a bleed fluid flow into a main fluid flow, wherein the bleed flow discharge device comprises an outer wall (135) defining a passage (137) for the bl...
https://drivepatents.com/patents/995636 · 28 Nov 2012
The present disclosure relates to a vortex reducer (100) for a bleed flow (104) in an axial turbomachine comprising a rotor disc (113). The vortex reducer may comprise one or more guide channels (122) arrangeable adjacent to a first side (113a) of the roto...