[특허]Gas turbine engine inner case including non-symmetrical bleed slots

UNITED TECHNOLOGIES CORPORATION

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Gas turbine engine inner case including non-symmetrical bleed slots

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/14 F01D-025/24 F02C-006/08 F02C-009/18 F01D-025/26 F02C-007/18 F02K-003/04 F04D-029/52
출원번호	US-0646549 (2013-03-05)
등록번호	US-10030539 (2018-07-24)
국제출원번호	PCT/US2013/029078 (2013-03-05)
국제공개번호	WO2014/098936 (2014-06-26)
발명자 / 주소	Ronan, Michael Carminati, Daniel
출원인 / 주소	UNITED TECHNOLOGIES CORPORATION
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 10

초록
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A compressor of a gas turbine engine includes a plurality of rotors rotatable about a central longitudinal axis, a plurality of stators, and a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators. The inner case wall includes a plurality of first slots located in a first section of the circumferential inner case wall and a plurality of second slots located in at least one second section of the circumferential inner case wall. A first area of each of the first slots is greater than a second area of each...

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1. A compressor of a gas turbine engine comprising: a plurality of rotors rotatable about a central longitudinal axis;a plurality of stators;a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators, the inner case wall including a plurality of first slots that are adjacent and are located in a first section of the circumferential inner case wall and a plurality of second slots that are adjacent and are located in a second section of the circumferential inner case wall, wherein an area of each of the plurality of first slots is greater than an area of each of the plurality of second slots, and wherein at least a portion of each first and second slot is axially aligned with respect to the central longitudinal axis; anda circumferential manifold located outwardly of the inner case wall and including a plurality of first ports and an environmental control system port, wherein the environmental control system port directs bleed air to an environmental control system and has a greater amount of bleed airflow than the plurality of first ports, and wherein each of the plurality of second slots is closer than each of the plurality of first slots to the environmental control system port. 2. The compressor as recited in claim 1 wherein the compressor is a low pressure compressor. 3. The compressor as recited in claim 1 wherein the plurality of first slots and the plurality of second slots are located after a fourth stage rotor. 4. The compressor as recited in claim 1 wherein the area of each of the plurality of second slots is about 90% of the area of each of the plurality of first slots. 5. The compressor as recited in claim 1 wherein the plurality of first ports comprises four mid-turbine frame/low pressure turbine ports that direct bleed air to a mid-turbine frame and a low pressure turbine. 6. The compressor as recited in claim 5 wherein each of the plurality of first slots are located closer than each of the plurality of second slots to the four mid-turbine frame/low pressure turbine ports. 7. The compressor as recited in claim 1 wherein the circumferential manifold includes a buffer port that directs bleed air to bearings and is situated between the environmental control system port and one of the plurality of first ports. 8. The compressor as recited in claim 1 including two third slots, wherein each of the two third slots have an area smaller than the area of each of the plurality of first slots and larger than the area of each of the plurality of second slots, and the first section and the second section meet at two locations, and each of third slots is located at one of the two locations. 9. The compressor as recited in claim 8 wherein the area of each of the two third slots is about 95% of the area of each of the plurality of first slots. 10. The compressor as recited in claim 8 wherein the plurality of first slots, the plurality of second slots, and the two third slots are equally spaced about the central longitudinal axis. 11. The compressor as recited in claim 8 comprising a buffer port that is separate from the plurality of first ports and the environmental control system port, wherein at least one of the two third slots is located closer to the buffer port than each of the plurality of first slots and each of the plurality of second slots. 12. The compressor as recited in claim 1: wherein the plurality of first ports comprises four mid-turbine frame/low pressure turbine ports that direct bleed air to a mid-turbine frame and a low pressure turbine,wherein the circumferential manifold includes a buffer port that directs bleed air to bearings, andwherein the environmental control system port has an area that is about four to about six times larger than an area of each of the four mid-turbine frame/low pressure turbine ports and an area of the buffer port. 13. A compressor of a gas turbine engine comprising: a plurality of rotors rotatable about a central longitudinal axis;a plurality of stators;a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators, the circumferential inner case wall including: a plurality of first slots that are adjacent and each have an area and are located in a first section of the circumferential inner case wall,a plurality of second slots that are adjacent and each have an area and are located in a second section of the circumferential inner case wall, andtwo third slots each having an area larger than the area of each of the plurality of second slots,wherein the area of each of the plurality of first slots is greater than the area of each of the plurality of second slots and the area of each of the two third slots, the first section and the second section meet at two locations, and each of the two third slots is located at one of the two locations, and wherein at least a portion of each first, second, and third slot is axially aligned with respect to the central longitudinal axis; anda circumferential manifold located outwardly of the circumferential inner case wall including an environmental control system port, wherein each of the plurality of second slots is located closer than each of the plurality of first slots to the environmental control system port. 14. The compressor as recited in claim 13 wherein the area of each of the plurality of second slots is about 90% of the area of each of the plurality of first slots, and the area of each of the two third slots is about 95% of the area of each of the plurality of first slots. 15. The compressor as recited in claim 13 wherein: the circumferential manifold includes:four mid-turbine frame/low pressure turbine ports that direct bleed air to a mid-turbine frame and a low pressure turbine, anda buffer port that directs bleed air to bearings,wherein each of the plurality of first slots are located closer than each of the plurality of second slots and the two third slots to the four mid-turbine frame/low pressure turbine ports, and the two third slots are located closer than each of the plurality of first slots and each of the plurality of second slots to the buffer port. 16. The compressor as recited in claim 13 wherein the plurality of first slots, the plurality of second slots, and the two third slots are equally spaced about the central longitudinal axis. 17. The compressor as recited in claim 16 wherein the compressor is a low pressure compressor. 18. The compressor as recited in claim 15, wherein the environmental control system port has a greater amount of airflow than the mid-turbine frame/low pressure turbine ports and the buffer port.

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Gas turbine engine inner case including non-symmetrical bleed slots

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Gas turbine engine inner case including non-symmetrical bleed slots

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