[특허]Aircraft combination engines complemental connection and operation

United Technologies Corporation

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Aircraft combination engines complemental connection and operation

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-041/00
미국특허분류(USC)	290/052; 290/047; 290/045; 290/051
출원번호	US-0801266 (2007-05-09)
등록번호	US-7485981 (2009-02-03)
발명자 / 주소	Schwarz,Frederick M. Berryann,Andrew P. Fentress,Brian M.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Kinney & Lange, P.A.
인용정보	피인용 횟수 : 6 인용 특허 : 4

초록
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A power generation system for propelling, and generating electrical power in, an aircraft, using a gas turbine engine coupled to a turbine starter/generator unit having therein an electrical machine capable of being selected to be alternatively a motor and an electrical power generator and having a coupling shaft extending therefrom to be engaged with the air compressor in the gas turbine engine and further having an interconnection conductor for electrical energization. An internal combustion engine provided as an intermittent combustion engine in the aircraft has an air intake coupled through an air transfer duct connected to the air compressor to allow the transfer of compressed air thereto, and has in connection therewith a supply starter/generator unit with a coupling shaft extending therefrom to be engaged with the intermittent combustion engine power shaft. An interconnection conductor therein for electrical energization is electrically interconnected with the turbine starter/generator unit interconnection conductor.

대표
청구항
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The invention claimed is: 1. A power generation system for propelling, and generating electrical power in, an aircraft, the system comprising: a gas turbine engine in an engine compartment in the aircraft having an air inlet open to the atmosphere, an air compressor, a combustor, a turbine and an exhaust exit nozzle open to the atmosphere all positioned along a fluids flow path passing therethrough for generating force, the air compressor having a compressor air transfer duct extending therefrom so as to be capable of providing compressed air therein and to the combustor; a turbine starter/generator unit having therein an electrical machine capable of being selected to be alternatively a motor and an electrical power generator and having a coupling shaft extending therefrom to be engaged with the air compressor in the gas turbine engine and further having an interconnection conductor for electrical energization; an internal combustion engine provided as an intermittent combustion engine in the aircraft having an air intake coupled to combustion chambers therein, a rotatable chamber shaft also coupled to those combustion chambers for generating force, and a fuel system for providing fuel to those combustion chambers, the compressor air transfer duct being connected to the air intake to transfer compressed air thereto, and a supply starter/generator unit having therein an electrical machine capable of being selected to be alternatively a motor and an electrical power generator and having a coupling shaft extending therefrom to be engaged with the chamber shaft and further having an interconnection conductor for electrical energization that is electrically interconnected with the turbine starter/generator unit interconnection conductor. 2. The combination of claim 1 wherein the turbine starter/generator unit has its interconnection conductor electrically energized by the supply starter/generator unit when the electrical machine in the turbine starter/generator unit is being operated as a motor, and has its interconnection conductor electrically energized by the air compressor in the gas turbine engine rotating its coupling shaft when the electrical machine in the turbine starter/generator unit is being operated as an electrical power generator. 3. The combination of claim 1 wherein the supply starter/generator unit has its interconnection conductor electrically energized by a battery when the electrical machine in the supply starter/generator unit is being operated as a motor, and has its interconnection conductor electrically energized by the intermittent combustion engine rotating its coupling shaft when the electrical machine in the supply starter/generator unit is being operated as an electrical power generator. 4. The combination of claim 1 further comprising a compressor control valve at least partially in the compressor air transfer duct which can be selectively directed to open more or close more to thereby selectively affect the passage of compressed air through the compressor air transfer duct. 5. The combination of claim 1 wherein the aircraft with gas turbine engine in the engine compartment therein has, from the air inlet in the aircraft open to the atmosphere, an inlet duct with a duct wall thereabout that is curved along its extent in extending from the air inlet along a curved path leading to the air compressor in that engine, and further comprises an inlet duct manifold positioned adjacent to the duct wall of the inlet duct on the air compressor side of a curve therein so as to permit drawing air therein that has previously entered the inlet duct and with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake such air can be selectively drawn from the inlet duct into that intermittent combustion engine air intake, and further comprising an inlet control valve at least partially in the inlet air transfer duct which can be selectively directed to open more or close more to thereby selectively affect the passage of air through the inlet air duct. 6. The combination of claim 5 further comprising an intake control valve at least partially in the intermittent combustion engine air intake at a location therein such that the air intake couplings to the combustion chambers are between the intake control valve and where the inlet air transfer duct is coupled to the intermittent combustion engine air intake, the intake control valve also being coupled to the atmosphere and which can be selectively directed to open more or close more to thereby selectively affect the passage of air through the intermittent combustion engine air intake. 7. The combination of claim 5 further comprising an inlet blower at least partially in the inlet air transfer duct which can be selectively directed to blow more or less air to thereby selectively affect the passage of air through the inlet air duct. 8. The combination of claim 7 wherein a rotor with blades in the blower is mechanically coupled through a coupler to the intermittent combustion engine output shaft. 9. The combination of claim 8 further comprising a speed changing gear set in the coupler. 10. The combination of claim 9 further comprising a clutch as part of the coupler which can be selectively directed to engage or disengage to thereby selectively complete the coupling to cause the blower rotor to be rotated. 11. The combination of claim 7 further comprising an inlet control valve at least partially in the inlet air transfer duct which can be selectively directed to open more or close more to thereby selectively affect the passage of air through the inlet air duct. 12. The combination of claim 5 wherein a location on the duct wall portion covered by the inlet duct manifold, where a plane passing through the curved path to intersect the duct wall has the intersection with the largest local curvature, has a greater density of the perforations than does some other parts of the duct wall located farther from such a plane. 13. The combination of claim 5 wherein the inlet duct manifold is positioned against the duct wall of the inlet duct so as to cover a space against a portion of that wall so that structural openings extending from the interior of the inlet duct open into that space. 14. The combination of claim 1 wherein the intermittent combustion engine has an exhaust outlet coupled to the combustion chambers therein and further comprises an intermittent combustion engine exhaust turbine positioned at the exhaust outlet and a supply electrical generator having a rotatable input shaft mechanically coupled through a coupler to an intermittent combustion engine exhaust turbine output shaft, the supply electrical generator having an output conductor which is electrically energized in response to rotation of the input shaft thereof. 15. The combination of claim 1 further comprising a supplemental electrical generator having a rotatable input shaft coupled through a coupler to the turbine of the gas turbine engine, the supplemental electrical generator having an output conductor which is electrically energized in response to rotation of the input shaft thereof. 16. The combination of claim 15 further comprising a clutch as part of the coupler which can be selectively directed to engage or disengage to thereby selectively complete the coupling to cause the supplemental electrical generator input shaft to be rotated. 17. The combination of claim 1 further comprising the turbine starter/generator unit with the rotatable operation coupling shaft coupled through a coupler to the air compressor of the gas turbine engine such that the turbine starter/generator unit can be selectively directed to rotate a rotor in the air compressor or to have a rotor in the starter to be rotated by the air compressor to generate electrical power, and yet further comprising a clutch as part of the coupler which can be selectively directed to engage or disengage to thereby selectively complete the coupling to allow the turbine starter/generator unit to be selectively directed to rotate a rotor in the air compressor or to allow a rotor in the starter to be rotated by the air compressor. 18. The combination of claim 1 wherein the intermittent combustion engine is positioned at least in part forward of the gas turbine engine in an aircraft propelled by the gas turbine engine. 19. The combination of claim 1 wherein the engine combination is in an aircraft propelled by the gas turbine engine that is a turbofan engine. 20. The combination of claim 1 wherein the aircraft is an unmanned stealth type aircraft.

이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 6

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Aircraft combination engines complemental connection and operation

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Aircraft combination engines complemental connection and operation

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