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Patent Searching and Data


Matches 301 - 350 out of 867

Document Document Title
WO2005042342A3
Method and systems for starting propeller driven aircraft and other devices. A system in accordance with one embodiment of the invention includes a removable fixture (130) that is coupled to the propeller (120) and has at least one porti...  
WO/2006/058774A2
A supply system (100) for the energy supply in an aircraft comprising an engine (101) for propelling an aircraft, a fuel cell (102) for supplying an aircraft with electric energy, a first fuel reservoir (103) for supplying the engine (10...  
WO/2006/034461A1
Methods and apparatus are provided for an exhaust duct (200) having an externally replaceable acoustic liner (208). The exhaust duct (200) includes a forward section (202) that is configured to be axially coupled with a bulkhead collar (...  
WO/2006/034460A1
The present invention provides a method for replacing an acoustic liner (210) through the forward end or aft end of an integrated exhaust duct muffler (“IEDM”) (200). The IEDM includes a bellmouth (202) coupled to a forward end of th...  
WO2005016748A3
An inlet door assembly and method for reducing noise from an auxiliary power unit (APU) (10) contained within an aircraft housing (12) is provided. The inlet assembly includes an inlet duct (21), an actuator (46) and a door (44). The inl...  
WO/2006/029058A1
Integrated axially varying engine mufflers, and associated methods and systems are disclosed. An arrangement in accordance with one embodiment of the invention includes a tailcone (120) having a tapering external surface (121), a cavity ...  
WO/2006/015857A1
A system comprises an H2/O2 steam generator (2) for generating superheated steam which is either fed directly to a gas turbine (8) to bring it to a rotary speed that is sufficient to result in a compressed-air ratio in the gas turbine th...  
WO/2005/113335A1
The invention pertains to a suction arrangement for drawing off boundary layers on an aircraft with a structure, the outer skin of which contains suction surfaces in critical flow areas, and with at least one air breathing engine. Bleed ...  
WO/2005/113334A1
An aircraft with a fluid-duct system for extraction of the laminar layer and/or blowing out of fluid at vulnerable places of the outer skin, wherein the fluid-duct system (26, 19, 18) by means of switchable valves (6, 4) is connectable t...  
WO/2005/098218A1
A gearbox (30, 130) for rotating a propeller in a selected one of a first or second direction provided. The second direction being opposite with respect to the first direction. The gearbox includes common gas turbine gear components sele...  
WO/2005/042342A2
Method and systems for starting propeller driven aircraft and other devices. A system in accordance with one embodiment of the invention includes a removable fixture (130) that is coupled to the propeller (120) and has at least one porti...  
WO/2005/016748A2
An inlet door assembly and method for reducing noise from an auxiliary power unit (APU) (10) contained within an aircraft housing (12) is provided. The inlet assembly includes an inlet duct (21), an actuator (46) and a door (44). The inl...  
WO/2004/074096A1
A fire protection apparatus (90, 92) for an oil cooler (26) in an aircraft auxiliary power unit compartment (10) adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oi...  
WO/2004/065215A1
A system and method for an engine bleed flow-sharing control system is disclosed. For a multi-engine bleed system, one (10) of the engines is selected as the master channel (15) such that the bleed air supply pressure of the control syst...  
WO2004037641A3
Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture (300) for providing power to an environmental control system (340a, 340b) includes an electric generator (316a, 316...  
WO/2004/037641A2
Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture (300) for providing power to an environmental control system (340a, 340b) includes an electric generator (316a, 316...  
WO/2003/053782A1
A ram air turbine power system (10) includes a ram air turbine (18) having a turbine shaft (22), turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft (28), for pr...  
WO/2003/037715A1
A passive cooling system for an auxiliary power unit (APU) installation (10) on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion (36) of a gas turbine engine (12) and an oil cooler (...  
WO2002040347A9
A system for supporting an auxiliary power unit (30) in an aircraft tailcone (20) wherein the auxiliary power unit is supported by a focalized suspension system (40a-40d) supporting the power unit, the focalized suspension system having ...  
WO2002066324A3
The present invention relates to an integrated aircraft system which comprises an aircraft frame (4), a primary gas turbine engine (14) mounted within the nacelle cowl (12), a secondary power system (30) incorporated within the nacelle c...  
WO/2002/098736A1
A ram air turbine system (10) provides liquid cooling of its generator (14) by employing a closed loop liquid cooling line originating from a pump (20) in the gearbox (16) of the system. In the preferred embodiment the pump may be a pito...  
WO2002034621A3
An aircraft fluid delivery device (10) including a piston assembly (20), a pilot assembly (22), and a control assembly (24). The control assembly (24) includes non-contact proximity sensors (S1, S2) that sense the positionof the piston (...  
WO2002040347A3
A system for supporting an auxiliary power unit (30) in an aircraft tailcone (20) wherein the auxiliary power unit is supported by a focalized suspension system (40a-40d) supporting the power unit, the focalized suspension system having ...  
WO/2002/079631A1
A tortuous path quiet exhaust eductor system may be mounted to a gas turbine engine, such as commercial aircraft APU. The system includes an oil cooler, eductor primary nozzle, oil cooler nozzle, and surge air dump nozzle. The primary no...  
WO/2002/074621A1
A swirl generator for creating bulk swirl in a compressor plenum (22) in the opposite direction to the direction of rotation of the compressor rotor (12). The generator includes a continuous flow pasageway formed by an inlet duct (40) an...  
WO/2002/066324A2
The present invention relates to an integrated aircraft system which comprises an aircraft frame (4), a primary gas turbine engine (14) mounted within the nacelle cowl (12), a secondary power system (30) incorporated within the nacelle c...  
WO2002023688A3
A data collection network and electrical power distribution network designed to reduce airplane wire weight and allow nearly complete wiring design and installation of wiring and equipment in the major structural sections of the airplane.  
WO2002016805A3
The present invention meets these objectives providing an IDG system that utilizes in flow series arrangement a scavenge pump (32), a spool valve (50) and a boost pump (44). When spool valve detects an interruption in the supply pressure...  
WO/2002/049913A1
A flow limiting apparatus (10') for limiting the flow of bleed air from an engine includes a plurality of parallel air flow paths therethrough, each flow path being provided by a venturi device (32) having a throat (36) and associated di...  
WO/2002/046040A1
The airflow distribution of bleed air extracted from a plurality of turbine engines (11, 13, 15, 17) is equalized by an airflow sharing system having electronic airflow sensors (49, 51, 53, 55) and closed-loop control algorithm to equali...  
WO/2002/040347A2
A system for supporting an auxiliary power unit (30) in an aircraft tailcone (20) wherein the auxiliary power unit is supported by a focalized suspension system (40a-40d) supporting the power unit, the focalized suspension system having ...  
WO/2002/034621A2
An aircraft fluid delivery device (10) including a piston assembly (20), a pilot assembly (22), and a control assembly (24). The control assembly (24) includes non-contact proximity sensors (S1, S2) that sense the positionof the piston (...  
WO2001062592A3
An air inlet assembly for bringing air to an auxiliary power unit (10) mounted in the APU compartment (12) of an aircraft (14). The assembly includes a duct (30) extending from an intake (32) contoured to conform to the aircraft fuselage...  
WO/2002/023688A2
A data collection network and electrical power distribution network designed to reduce airplane wire weight and allow nearly complete wiring design and installation of wiring and equipment in the major structural sections of the airplane.  
WO/2002/016805A2
The present invention meets these objectives providing an IDG system that utilizes in flow series arrangement a scavenge pump (32), a spool valve (50) and a boost pump (44). When spool valve detects an interruption in the supply pressure...  
WO/2001/062592A2
An air inlet assembly for bringing air to an auxiliary power unit (10) mounted in the APU compartment (12) of an aircraft (14). The assembly includes a duct (30) extending from an intake (32) contoured to conform to the aircraft fuselage...  
WO/2001/061768A1
A thermoelectric power generator for an aircraft including a heat source or hot air exhaust air flow (30), characterized as providing thermal energy, at least one thermoelectric module (32), including a plurality of thermoelectric elemen...  
WO/2001/047100A1
An auxiliary power unit ('APU') system and methods used to bring such system on-line and off-line are disclosed. An APU generator (18) forming part of an APU system (10), is brought 'on-line' smoothly in order to replace a primary genera...  
WO/2001/034464A2  
WO2000059780A3
An improved aircraft (10) is provided through the use of an improved hydraulic system (12) which incorporates a flywheel peaking unit (28) that stores energy during periods when the aircraft is demanding less hydraulic power than the rem...  
WO/2000/059780A2
An improved aircraft (10) is provided through the use of an improved hydraulic system (12) which incorporates a flywheel peaking unit (28) that stores energy during periods when the aircraft is demanding less hydraulic power than the rem...  
WO/1999/046167A1
An APU compartment (80) drain system is provided that ensures thorough draining of fluids from the compartment (80) that may otherwise accumulate therein. Such drainage is achieved despite the presence of a predetermined range of negativ...  
WO/1999/041146A1
An electrical power system (10) for an aircraft includes an ac generator bus (16), an air conditioning system ('ACS') generator (42) and a main engine generator (46). The ACS generator (42) supplies primary ac power to the bus (16) while...  
WO/1999/014116A1
A ram air turbine includes a reaction turbine and an electrical generator that is driven by shaft power of the reaction turbine. A scoop directs a flow of ram air to an inlet of the reaction turbine and creates a pressure head for the re...  
WO/1999/012810A1
The need for engine bleed air in a cabin pressurizing/ventilation ECS system for aircraft is avoided in a construction including a pressurizable aircraft cabin (10) having a cabin air inlet (20) and a cabin air outlet (22). The system in...  
WO/1998/048162A1
The present invention provides a novel aircraft subsystem that provides both electricity and conditioned air to the aircraft independently of the main engines. The subsystem includes turbomachinery comprising three independently rotating...  
WO/1998/013258A1
The present invention provides a multi-mode secondary power unit (14) comprising a first starter/generator unit (10) operably coupled to a shaft (20). The first starter/generator motor (10) is operable in a motor mode for causing rotatio...  
WO/1998/005553A1
The present invention provides a tailcone and power assembly (10) mountable to the body of an aircraft using a height adjustable dolly (11). The tailcone assembly comprises a longitudinal support member (14), a gas turbine engine (12) mo...  
WO/1995/027655A1
An environmental control system has an air cycle machine that includes a compressor (38), a cooling turbine (34), a motor/generator (36), and a power turbine (40) all mounted on a single shaft (32). The power turbine receives bleed air f...  
WO/1994/019606A1
An actuator suitable for use as an ejection jack (10) for deploying an aircraft mounted ram air turbine (118) is provided. The actuator includes a force transmitting reciprocating member (12) mounted for reciprocating movement along a pa...  

Matches 301 - 350 out of 867