[특허]Gas turbine engine and heat exchange system

Rolls-Royce North American Technologies, Inc.

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특허 상세정보

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Gas turbine engine and heat exchange system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/14 F02C-007/18 F02C-007/12 F02K-003/06 F01D-025/12
미국특허분류(USC)	060/266; 060/782; 060/785
출원번호	US-0979028 (2010-12-27)
등록번호	US-8910465 (2014-12-16)
발명자 / 주소	Snyder, Douglas J.
출원인 / 주소	Rolls-Royce North American Technologies, Inc.
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 4 인용 특허 : 17

초록

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine heat exchange system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and heat exchange systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

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1. A gas turbine engine, comprising: an engine core;a first fan operable to generate a first air stream at a first pressure downstream thereof;a second fan positioned downstream of the first fan, the second fan operable to receive a portion of the first air stream and generate a second air steam at a second pressure;a fan bypass duct operative to direct a portion of the second air stream to a bypass stream around the engine core;an other fan bypass duct operative to direct a portion of the first air stream to an other bypass stream around the engine core; andan adaptive heat exchange system operative to cool an object of cooling using the air from the fan bypass duct and/or the other fan bypass duct as a cooling medium;wherein the gas turbine engine is configured to operate in a first mode in which the second pressure in the fan bypass duct is greater than the first pressure in the other fan bypass duct, and in a second mode in which the second pressure in the fan bypass duct is substantially the same as the first pressure in the other fan bypass duct; andwherein in the first mode the adaptive heat exchange system routes cooling medium from the fan bypass duct to the other fan bypass duct, and in the second mode the adaptive heat exchange system routes cooling medium from the other fan bypass duct to the other fan bypass duct. 2. The gas turbine engine of claim 1, wherein the adaptive heat exchange system includes a heat exchanger having a cooling medium inlet and a cooling medium outlet; wherein the cooling medium inlet is selectively exposed to a selected one or both of the fan bypass duct and the other fan bypass duct to receive a cooling medium; and wherein the cooling medium outlet is positioned to discharge the cooling medium into the other fan bypass duct. 3. The gas turbine engine of claim 2, wherein the heat exchanger is hinged to selectively expose the cooling medium inlet to the selected one or both of the fan bypass duct and the other fan bypass duct. 4. The gas turbine engine of claim 1, wherein the adaptive heat exchange system includes a heat exchanger operative to exchange heat in a parallel flow mode and a cross flow mode. 5. The gas turbine engine of claim 4, wherein the heat exchanger includes a fin operative to transfer heat from the object of cooling; wherein the parallel flow mode directs the cooling medium in a first direction parallel to the fin; and wherein the cross flow mode directs the cooling medium in a second direction not parallel to the fin. 6. The gas turbine engine of claim 5, wherein the heat exchanger includes a first cooling medium inlet for receiving the cooling medium in the parallel flow mode; and wherein the heat exchanger includes a second cooling medium inlet for receiving the cooling medium in the cross flow mode. 7. The gas turbine engine of claim 6, wherein the second cooling medium inlet includes an opening operative to impinge the cooling medium onto the fin. 8. The gas turbine engine of claim 1, wherein the adaptive heat exchange system is operative to cool the object of cooling using air by selecting the air from one or both of the fan bypass duct and the other fan bypass duct in response to an engine operating condition. 9. The gas turbine engine of claim 8, wherein the adaptive heat exchange system is passively controlled. 10. The gas turbine engine of claim 8, wherein the adaptive heat exchange system is actively controlled. 11. A gas turbine engine, comprising: a first airway carrying a first air stream at a first pressure generated by a first fan;a second airway carrying a second air stream at a second pressure generated by a second fan, wherein the first fan receives airflow from the second fan; andan adaptive heat exchange system operative to cool an object of cooling using air from the first airway and the second airway as a cooling medium;wherein the adaptive heat exchange system includes a heat exchanger having a first cooling medium inlet and a second cooling medium inlet; wherein the first cooling medium inlet is adapted to receive the cooling medium from one of the first airway and the second airway; and wherein the second cooling medium inlet is adapted to receive the cooling medium from the other of the first airway and the second airway. 12. The gas turbine engine of claim 11, wherein the first airway is a first working fluid main flowpath; and wherein the second airway is a second working fluid main flowpath. 13. The gas turbine engine of claim 11, wherein the heat exchanger employs impingement cooling. 14. The gas turbine engine of claim 11, wherein the adaptive heat exchange system includes a valve operative to control flow through one of the first cooling medium inlet and the second cooling medium inlet. 15. The gas turbine engine of claim 14, wherein the adaptive heat exchange system includes a cooling medium exit; and wherein the valve is positioned in the cooling medium exit. 16. A gas turbine engine, comprising: a compressor including a core passageway for routing core airflow therethrough, wherein the core airflow is pressurized by first and second fans prior to entering into the compressor;a combustor in fluid communication with the compressor;a turbine in fluid communication with the combustor;a first bypass duct operative to direct air therethrough;a second bypass duct disposed radially outward from the first bypass duct and operative to direct air therethrough;an adaptive heat exchange system for cooling air from the compressor with air streams generated by the first and/or second fans prior to being discharged into the turbine;wherein the adaptive heat exchange system is configured to adapt to first and second modes of operation, wherein in the first mode of operation the adaptive heat exchange system receives air as a cooling medium from the first fan bypass duct and expels the cooling medium into the second fan bypass duct, and in the second mode of operation the adaptive heat exchange system receives air as a cooling medium from the second fan bypass duct and expels the cooling medium into the second fan bypass duct. 17. The gas turbine engine of claim 16, wherein the air cooled by the adaptive heat exchange system is discharged into the turbine as cooling air. 18. The gas turbine engine of claim 16, wherein the adaptive heat exchange system is configured to receive a cooling medium from more than one cooling medium source, wherein in the first mode of operation the adaptive heat exchange system receives air from both the first fan bypass duct and the second fan bypass duct and expels the cooling medium into the second fan bypass duct. 19. The gas turbine engine of claim 18, wherein the adaptive heat exchange system is actively controlled to select a cooling medium source.

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 4

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Gas turbine engine and heat exchange system

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Gas turbine engine and heat exchange system

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