About 149 results
https://drivepatents.com/patents/977230 · 19 Mar 2014
A rotor assembly comprises an annular sleeve (30) having an inner member (34) connected around a shaft (20) to rotate together therewith and an outer member (36) with a first end connected to the inner member (34). The outer member (36) defines an annular ...
https://drivepatents.com/patents/977214 · 19 Mar 2014
A system for pressurizing a generator (30) in a gas turbine engine (10) includes a fluid valve (34) for permitting or inhibiting airflow into a housing of the generator (30). The fluid valve (34) may be in fluid communication with an air source (14) within...
https://drivepatents.com/patents/977213 · 19 Mar 2014
A system for cooling a generator (60) mounted in the tail-cone (58) of an engine comprises a fairing (66), which receives through an inlet (68) thereof air from a bypass duct (38) and directs the bypass air (40) towards a cavity (62) of the tail-cone (58) ...
https://drivepatents.com/patents/979390 · 22 Jan 2014
A compound cycle engine (10) has at least one rotary unit (12) defining an internal combustion engine, a velocity turbine (26) in proximity of each unit (12), and a turbocharger (18). The exhaust port of each rotary unit (12) is in fluid communication with...
https://drivepatents.com/patents/979389 · 22 Jan 2014
A compound cycle engine (10) has an output shaft (16); at least two rotary units (12) each defining an internal combustion engine, a velocity turbine (26), and a turbocharger (18). The velocity turbine (26) includes a rotor in driving engagement with the o...
https://drivepatents.com/patents/979645 · 15 Jan 2014
A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft, where the engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control sy...
https://drivepatents.com/patents/982477 · 30 Oct 2013
A compressor for a gas turbine engine with variable inlet guide vanes (42) each defining an airfoil portion (48) twisted such that at each location of the airfoil portion (48) along the pivot axis (P), an angle (±) is defined between a respective chord ex...
https://drivepatents.com/patents/983897 · 2 Oct 2013
A gas turbine engine recuperator system (30) includes a heat recuperator (32) positioned in a gas turbine exhaust gas duct (28) for recovering heat from turbine exhaust gases (48) to preheat a compressor flow being supplied to the combustor (26). A continu...
https://drivepatents.com/patents/987695 · 7 Aug 2013
A rotary internal combustion engine (10) has an insert opening (36) defined in a hot area of one of the walls (18) of the stator body (12) and in communication with its internal cavity (20). At least one groove (58) is defined within the opening (36) aroun...
https://drivepatents.com/patents/984895 · 5 Jun 2013
A system for changing a speed ratio between a compressor boost stage (12) and at least one power turbine (16) of a gas turbine engine (10) comprises a coupling device (20) configured to selectively transmit energy from the at least one power turbine (16) t...