[특허]Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers

Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/18 F02C-007/06 F02C-007/14 F01D-009/04 F01D-009/06 F01D-005/02 F02C-003/04 F02C-007/04 F01D-025/24 F04D-029/54 F01D-025/12 F01D-017/10 F02C-006/08
출원번호	US-0771061 (2014-02-28)
등록번호	US-9957895 (2018-05-01)
국제출원번호	PCT/US2014/019567 (2014-02-28)
국제공개번호	WO2014/134519 (2014-09-04)
발명자 / 주소	Suciu, Gabriel L. Ackermann, William K.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	O'Shea Getz P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 69

초록 ▼

A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.

대표청구항 ▼

1. A gas turbine engine comprising: a compressor section;a combustor section with a multiple of pre-swirlers;a diffuser case module with a multiple of struts within an annular flow path from said compressor section to said combustor section, at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path; anda manifold in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers;wherein said manifold communicates a temperature tailored airflow through a heat exchanger. 2. The gas turbine engine as recited in claim 1, wherein said manifold communicates said temperature tailored airflow from said heat exchanger as buffer air. 3. The gas turbine engine as recited in claim 2, wherein said buffer air is communicated through a buffer passage to a bearing compartment. 4. The gas turbine engine as recited in claim 1, wherein said mid-span pre-diffuser inlet is located radially outboard of a central span section of said multiple of struts. 5. The gas turbine engine as recited in claim 1, wherein said mid-span pre-diffuser inlet is located radially inboard of a central span section of said multiple of struts. 6. The gas turbine engine as recited in claim 1, wherein said mid-span pre-diffuser inlet is located radially outboard and radially inboard of a central span section of said multiple of struts. 7. A method of communicating an airflow within a gas turbine engine, comprising: tapping a pre-diffuser airflow as a pre-defined temperature tailored airflow;communicating the pre-defined temperature tailored airflow to a multiple of pre-swirlers; andcommunicating the pre-defined temperature tailored airflow through a heat exchanger. 8. The method as recited in claim 7, further comprising communicating the pre-diffuser airflow through at least one of a multiple of struts. 9. The method as recited in claim 7, further comprising communicating the pre-defined temperature tailored airflow through a manifold. 10. The method as recited in claim 7, further comprising communicating the temperature tailored airflow from the heat exchanger as buffer air. 11. The method as recited in claim 10, further comprising communicating the buffer air to a bearing compartment. 12. The method as recited in claim 7, further comprising tapping the pre-diffuser airflow adjacent to a shroud. 13. The method as recited in claim 7, further comprising tapping the pre-diffuser airflow adjacent to an inner shroud. 14. The method as recited in claim 7, further comprising tapping the pre-diffuser airflow adjacent to an outer shroud. 15. A gas turbine engine, comprising: a compressor section;a combustor section including a plurality of pre-swirlers;a diffuser case module configured with a plurality of struts and an annular flow path between the compressor section and the combustor section, the plurality of struts within the annular flow path, and at least one of the plurality of struts includes a pre-diffuser inlet in communication with the annular flow path; anda manifold in communication with the pre-diffuser inlet and a first of the plurality of pre-swirlers, the manifold directing air received from the pre-diffuser inlet to the first of the plurality of pre-swirlers independent of the annular flow path.

이 특허에 인용된 특허 (69)

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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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연합인증

Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers 원문보기

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Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers 원문보기

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연구과제 타임라인

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