Turbo-compressor system and method for extracting energy from an aircraft engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-013/08
F02C-007/32
F25B-027/00
F25B-031/02
B64D-041/00
B64D-013/06
출원번호
US-0203533
(2014-03-10)
등록번호
US-9656756
(2017-05-23)
발명자
/ 주소
Atkey, Warren A.
출원인 / 주소
The Boeing Company
인용정보
피인용 횟수 :
1인용 특허 :
3
초록▼
A turbo-compressor (TC) system for extracting energy from an aircraft engine. The TC system has a TC assembly with a turbine mechanically coupled to at least one compressor. The TC system has a TC inlet in fluid communication with a bleed air system in the aircraft engine and a TC outlet in fluid co
A turbo-compressor (TC) system for extracting energy from an aircraft engine. The TC system has a TC assembly with a turbine mechanically coupled to at least one compressor. The TC system has a TC inlet in fluid communication with a bleed air system in the aircraft engine and a TC outlet in fluid communication with an air conditioning (AC) pack of an aircraft air conditioning system and configured to extract reduced temperature pack inlet air from the TC assembly into the air conditioning pack. The TC system has a ram air inlet coupled to the at least one compressor. The TC system has a TC control valve, and a TC check valve or a TC shutoff valve, both coupled to the TC assembly via a plurality of connective ducts. The TC system extracts energy from the bleed air to reduce bleed air flow and AC pack ram air usage.
대표청구항▼
1. A turbo-compressor (TC) system for extracting energy from an aircraft engine, the turbo-compressor system comprising: a turbo-compressor assembly comprising a turbine mechanically coupled to at least one compressor;a turbo-compressor inlet in fluid communication with a bleed air system in the air
1. A turbo-compressor (TC) system for extracting energy from an aircraft engine, the turbo-compressor system comprising: a turbo-compressor assembly comprising a turbine mechanically coupled to at least one compressor;a turbo-compressor inlet in fluid communication with a bleed air system in the aircraft engine, to intake bleed air from the bleed air system into the turbo-compressor assembly;a turbo-compressor outlet in fluid communication with an air conditioning pack of an aircraft air conditioning system, to extract reduced temperature pack inlet air from the turbo-compressor assembly directly into the air conditioning pack, the reduced temperature pack inlet air comprising one of, a mixture of turbine outlet air and compressor outlet air, and a mixture of turbine outlet air, compressor outlet air, and bleed air through a pack flow control valve for the air conditioning pack, the air conditioning pack being separate from the turbo-compressor assembly and further cooling the reduced temperature pack inlet air, and the air conditioning pack being coupled to a pack heat exchanger having one or more heat exchangers;the at least one compressor coupled to at least one of, a ram air inlet to intake ram air by the at least one compressor, and a recirculated cabin air duct to intake recirculated cabin air from an aircraft cabin by the at least one compressor; and,a turbo-compressor control valve, and a turbo-compressor check valve or a turbo-compressor shutoff valve, both coupled to the turbo-compressor assembly via a plurality of connective ducts,wherein the turbo-compressor system extracts energy from the bleed air. 2. The turbo-compressor system of claim 1 further comprising an electric motor mechanically coupled between the turbine and the at least one compressor, the electric motor augmenting power to the at least one compressor. 3. The turbo-compressor system of claim 1 further comprising one or more temperature sensors positioned at a compressor outlet of the at least one compressor, the one or more temperature sensors providing overheat protection of compressor outlet air. 4. The turbo-compressor system of claim 1 wherein the turbo-compressor assembly comprises a first compressor and a second compressor. 5. The turbo-compressor system of claim 4 further comprising an intercooler heat exchanger coupled between the first compressor and the second compressor, the intercooler heat exchanger maintaining a ram air temperature of the ram air below a fuel auto-ignition temperature limit. 6. The turbo-compressor system of claim 4 wherein the first compressor is coupled to one of, the ram air inlet, and the recirculated cabin air duct. 7. The turbo-compressor system of claim 1 wherein the turbo-compressor system operates in parallel with a pack flow control valve for the air conditioning pack. 8. The turbo-compressor system of claim 1 wherein the turbine has a turbine inlet for receiving the bleed air and extracts the energy from the bleed air passing through the turbine, to generate power to drive the at least one compressor. 9. The turbo-compressor system of claim 1 wherein the turbo-compressor system is coupled to the air conditioning pack having an air cycle system. 10. The turbo-compressor system of claim 1 wherein the ram air inlet comprises a ram air inlet scoop or a ram air inlet bypass duct integral with a ram air system of an aircraft. 11. The turbo-compressor system of claim 1 wherein the turbo-compressor system extracts energy from the bleed air to reduce bleed air flow needed for the air conditioning pack, resulting in reduced power requirements for the aircraft air conditioning system and reduced air conditioning pack ram air usage. 12. An aircraft comprising: at least one wing;one or more aircraft engines coupled to the at least one wing, each aircraft engine having a bleed air system for generating bleed air;a fuselage defining an interior volume having an aircraft cabin and a pack bay separate from the aircraft cabin;an aircraft air conditioning system positioned in the pack bay and in fluid communication with the aircraft cabin, the aircraft air conditioning system comprising: an air conditioning pack; and,a turbo-compressor (TC) system comprising: a turbo-compressor assembly comprising a turbine mechanically coupled to at least one compressor;a turbo-compressor inlet in fluid communication with the bleed air system, to intake bleed air from the bleed air system into the turbo-compressor assembly;a turbo-compressor outlet in fluid communication with the air conditioning pack, to extract reduced temperature pack inlet air from the turbo-compressor assembly directly into the air conditioning pack, the reduced temperature pack inlet air comprising one of, a mixture of turbine outlet air and compressor outlet air, and a mixture of turbine outlet air, compressor outlet air, and bleed air through a pack flow control valve for the air conditioning pack, the air conditioning pack being separate from the turbo-compressor assembly and further cooling the reduced temperature pack inlet air, and the air conditioning pack being coupled to a pack heat exchanger having one or more heat exchangers;the at least one compressor coupled to at least one of, a ram air inlet to intake ram air by the at least one compressor, and a recirculated cabin air duct to intake recirculated cabin air from the aircraft cabin by the at least one compressor; and,a turbo-compressor control valve, and a turbo-compressor check valve or a turbo-compressor shutoff valve, both coupled to the turbo-compressor assembly via a plurality of connective ducts,wherein the turbo-compressor system extracts energy from the bleed air. 13. The aircraft of claim 12 wherein the turbo-compressor system further comprises one or more of an electric motor mechanically coupled between the turbine and the at least one compressor; one or more temperature sensors positioned at a compressor outlet of the at least one compressor; and an intercooler heat exchanger coupled to the at least one compressor. 14. The aircraft of claim 12 wherein the turbo-compressor assembly comprises a first compressor and a second compressor, and the first compressor is coupled to one of, the ram air inlet, and the recirculated cabin air duct. 15. The aircraft of claim 12 wherein the turbo-compressor system is coupled to the air conditioning pack having an air cycle system. 16. The aircraft of claim 12 wherein the turbo-compressor system extracts energy from the bleed air to reduce bleed air flow needed for the air conditioning pack, resulting in reduced power requirements for the aircraft air conditioning system and reduced air conditioning pack ram air usage. 17. A method of extracting energy from an aircraft engine, the method comprising the steps of: installing a turbo-compressor (TC) system in an aircraft air conditioning system of an aircraft, the turbo-compressor system comprising: a turbo-compressor assembly disposed between a turbo-compressor inlet and a turbo-compressor outlet and comprising a turbine mechanically coupled to at least one compressor;the turbo-compressor inlet in fluid communication with a bleed air system in the aircraft engine, to intake bleed air from the bleed air system into the turbo-compressor assembly;the turbo-compressor outlet in fluid communication with an air conditioning pack of an aircraft air conditioning system, to extract reduced temperature pack inlet air from the turbo-compressor assembly directly into the air conditioning pack, the reduced temperature pack inlet air comprising one of, a mixture of turbine outlet air and compressor outlet air, and a mixture of turbine outlet air, compressor outlet air, and bleed air through a pack flow control valve for the air conditioning pack, the air conditioning pack being separate from the turbo-compressor assembly and further cooling the reduced temperature pack inlet air to provide pressurization, ventilation, and temperature control to the aircraft, and the air conditioning pack being coupled to a pack heat exchanger having one or more heat exchangers;the at least one compressor coupled to at least one of, a ram air inlet, and a recirculated cabin air duct; and,a turbo-compressor control valve, and a turbo-compressor check valve or a turbo-compressor shutoff valve, both coupled to the turbo-compressor assembly via a plurality of connective ducts;using the turbine of the turbo-compressor system to extract energy from the bleed air to obtain turbine outlet air and extracted energy;driving the at least one compressor with the extracted energy to intake and compress one of, ram air from the ram air inlet to obtain compressor outlet air, and recirculated cabin air from an aircraft cabin through a recirculated cabin air duct to obtain compressor outlet air;using the turbo-compressor system to reduce bleed air flow needed for the air conditioning pack in the aircraft air conditioning system, thus reducing power requirements for the aircraft air conditioning system; and,mixing the turbine outlet air and the compressor outlet air in the turbo-compressor system to obtain the reduced temperature pack inlet air and a reduced air conditioning pack ram air usage. 18. The method of claim 17 further comprising the step of mechanically coupling an electric motor between the turbine and the at least one compressor to augment power to the at least one compressor. 19. The method of claim 17 further comprising the step of positioning one or more temperature sensors at a compressor outlet of the at least one compressor to provide overheat protection of the compressor outlet air. 20. The method of claim 17 further comprising the step of coupling an intercooler heat exchanger to the turbo-compressor assembly to maintain a ram air temperature of the ram air below a fuel auto-ignition temperature limit. 21. The method of claim 17 wherein the step of installing the turbo-compressor system in the aircraft air conditioning system of the aircraft comprises coupling the turbo-compressor system to the air conditioning pack having an air cycle system. 22. The method of claim 17 wherein the step of installing the turbo-compressor (TC) system comprises installing the turbo-compressor (TC) system having the turbo-compressor assembly with a first compressor and a second compressor, the first compressor coupled to one of, the ram air inlet, and the recirculated cabin air duct. 23. The method of claim 17 further comprising the step of controlling flow of the reduced temperature pack inlet air from the turbo-compressor system into the air conditioning pack by opening the turbo-compressor control valve and closing one or more pack flow control valves for the air conditioning pack. 24. The method of claim 17 wherein the step of using the turbo-compressor system to reduce bleed air flow further comprises simultaneously opening both a pressure regulating shutoff valve and an over pressure valve in the bleed air system.
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이 특허에 인용된 특허 (3)
Coffinberry George A. (West Chester OH), Aircraft gas turbine engine bleed air energy recovery apparatus.
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