System and method for controlling the temperature and infrared signature of an engine
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/38
F02K-001/00
F02K-001/46
F02K-003/105
F02K-003/00
F02C-007/224
F02C-007/22
출원번호
US-0268031
(2005-11-07)
등록번호
US-7478525
(2009-01-20)
발명자
/ 주소
Iya,Sridhar K.
Roe,George M.
출원인 / 주소
The Boeing Company
대리인 / 주소
Alston & Bird LLP
인용정보
피인용 횟수 :
13인용 특허 :
10
초록▼
A system and method for cooling at least a portion of an engine are provided. The engine is cooled using a fuel, such as a high heat sink fuel, that is subsequently used for combustion in the engine. The fuel can be used to cool one or more of the gases and/or components in the engine, thereby cool
A system and method for cooling at least a portion of an engine are provided. The engine is cooled using a fuel, such as a high heat sink fuel, that is subsequently used for combustion in the engine. The fuel can be used to cool one or more of the gases and/or components in the engine, thereby cooling the engine including an exhaust nozzle. For example, the fuel can be circulated through one or more heat exchanging devices that are disposed inside or outside a passage of the engine, and the fuel can absorb thermal energy from the engine or air that flows in the engine passage. In any case, the cooling of the engine can result in a reduction to the infrared signature of the engine.
대표청구항▼
That which is claimed: 1. A system for reducing the infrared signature of an engine, the system comprising: an engine passage extending between an inlet end and an exhaust end and structured to receive at least one gas therethrough; a fuel source configured to supply a fuel for combustion in the en
That which is claimed: 1. A system for reducing the infrared signature of an engine, the system comprising: an engine passage extending between an inlet end and an exhaust end and structured to receive at least one gas therethrough; a fuel source configured to supply a fuel for combustion in the engine passage; at least one combustion device in the engine passage configured to combust the fuel in the engine passage; a nozzle at the exhaust end of the engine passage structured to receive the gas from the engine passage and discharge the gas; an augmentor configured to receive fuel and to discharge the fuel into the engine passage for combustion at a longitudinal location between the at least one combustion device and the nozzle; a heat exchanger positioned outside the engine passage and configured to receive a flow of air and a flow of the fuel before the fuel is combusted, and transfer thermal energy from the air to the fuel to cool the air; and a turbocooler having a compressor and a turbine, the compressor of the turbocooler being configured to compress the air and provide the air to the heat exchanger, and the turbine configured to receive the air from the heat exchanger, expand and cool the air, and deliver the cooled air to the engine passage at an axial location proximate the augmentor, thereby cooling the nozzle and reducing the infrared signature of the engine. 2. A system according to claim 1 wherein the heat exchanger is configured to deliver the cooled air into the engine passage at the nozzle. 3. A system according to claim 1 wherein the heat exchanger is configured to receive the air from a compressor in the engine passage, the air being compressed by the compressor in the engine passage during operation of the engine. 4. A system according to claim 1 wherein the heat exchanger is configured to heat the fuel to a temperature of at least 300° F. 5. A system according to claim 1 wherein the fuel source is configured to supply a high heat sink fuel that is stable at a temperature greater than 300° F. 6. A system according to claim 1, further comprising a precooler heat exchanger configured to receive a flow of compressed air from a compressor in the engine passage and a flow of the fuel, the air being compressed by the compressor in the engine passage during operation of the engine, and the precooler heat exchanger transferring thermal energy from the air to the fuel. 7. A system according to claim 1, further comprising a transducer disposed in the heat exchanger between the flow of the air and the flow of the fuel, the transducer configured to convert thermal energy from the air to electricity. 8. A system for reducing the infrared signature of an engine, the system comprising: an engine passage defining a central passage and a fan duct extending in a longitudinal direction of the engine passage between an inlet end and an exhaust end; a fuel source configured to supply a fuel for combustion in the central passage; a first compressor in the central passage configured to provide a flow of compressed air for combustion with the fuel in the central passage; at least one combustion device in the central passage configured to combust the fuel with the compressed air to form an exhaust gas; a nozzle at the exhaust end of the engine passage structured to receive the exhaust gas from the central passage and discharge the exhaust gas; an augmentor configured to receive fuel and to discharge the fuel into the engine passage for combustion at a longitudinal location between the at least one combustion device and the nozzle; a heat exchanger disposed outside the engine passage and configured to receive a flow of the fuel from the fuel source and circulate the fuel to the combustion device, the heat exchanger also being configured to receive a flow of air, and transfer thermal energy from the air to the fuel to cool the air and a turbocooler having a second compressor and a turbine, the second compressor being configured to receive air from the first compressor, compress the air, and provide the air to the heat exchanger, the turbine being configured to receive the air from the heat exchanger, expand and cool the air, and deliver the cooled air to the engine passage at an axial location proximate the augmentor to thereby cool the nozzle and reduce the infrared signature of the engine. 9. A system according to claim 8, further comprising a precooler heat exchanger configured to receive a flow of compressed air from the first compressor in the engine passage and a flow of the fuel, the precooler heat exchanger transferring thermal energy from the air to the fuel, and the second compressor of the turbocooler being configured to receive the air from the first compressor via the precooler. 10. A system according to claim 8 wherein the heat exchanger is configured to heat the fuel to a temperature of at least 300° F. 11. A system according to claim 8, further comprising a transducer disposed in the heat exchanger and configured to be heated by the air therein and convert thermal energy from the air to electricity. 12. A system according to claim 8 wherein the fuel source is configured to supply a high heat sink fuel that is stable at a temperature greater than 300° F. 13. A method for reducing the infrared signature of an engine, the method comprising: compressing air in an engine passage; combusting fuel and a portion of the compressed air in the engine passage to form an exhaust gas; adding additional fuel to the exhaust gas with an augmentor and combusting the additional fuel to form an exhaust that is discharged from the engine through a nozzle; compressing a flow of air in a compressor of a turbocooler; circulating a flow of the fuel through a heat exchanger disposed outside the engine passage; delivering the compressed flow of air from the compressor of the turbocooler to the heat exchanger and thereby transferring thermal energy in the heat exchanger from the air to the fuel to cool the air; delivering the fuel from the heat exchanger to the combustion device for combustion; expanding the air from the heat exchanger in a turbine of the turbocooler to thereby cool the air; and delivering the cooled air from the turbine of the turbocooler to the engine passage at an axial location proximate the augmentor to thereby cool the nozzle and reduce the infrared signature of the engine. 14. A method according to claim 13 further comprising circulating the air through a precooler heat exchanger before the air is compressed in the compressor of the turbocooler, the precooler receiving a flow of fuel and transferring thermal energy from the air to the fuel. 15. A method according to claim 13 wherein said circulating step comprises heating the fuel to a temperature of at least 300° F. 16. A method according to claim 13, further comprising heating a transducer with the air in the heat exchanger and converting thermal energy from the air to electricity. 17. A method according to claim 13, further comprising providing the fuel as a high heat sink fuel that that is stable at a temperature greater than 300° F.
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이 특허에 인용된 특허 (10)
Glickstein Marvin R. (North Palm Beach FL), Aircraft cooling method.
Bulin, Guillaume; Dittmar, Jan, Method for controlling thermal effluents generated by an aircraft and cooling device for an aircraft implementing said method.
Chandler, Christopher, Optimization of gas turbine combustion systems low load performance on simple cycle and heat recovery steam generator applications.
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