Ambient air cooling arrangement having a pre-swirler for gas turbine engine blade cooling
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/12
F01D-005/14
F01D-009/06
F02C-007/12
F01D-005/18
F01D-005/08
F01D-011/00
출원번호
US-0766909
(2013-02-14)
등록번호
US-8926267
(2015-01-06)
발명자
/ 주소
Lee, Ching-Pang
Tham, Kok-Mun
Schroeder, Eric
Meeroff, Jamie
Miller, Jr., Samuel R.
Marra, John J.
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
1인용 특허 :
24
초록▼
A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a pluralit
A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.
대표청구항▼
1. A gas turbine engine, comprising: an ambient-air cooling circuit comprising a cooling channel disposed in a turbine blade and in fluid communication with a source of ambient air that provides cooling fluid: anda pre-swirler, comprising: an inner shroud;an outer shroud; anda plurality of guide van
1. A gas turbine engine, comprising: an ambient-air cooling circuit comprising a cooling channel disposed in a turbine blade and in fluid communication with a source of ambient air that provides cooling fluid: anda pre-swirler, comprising: an inner shroud;an outer shroud; anda plurality of guide vanes, each spanning from the inner shroud to the outer shroud,wherein circumferentially adjacent guide vanes define respective nozzles there between, the nozzles defining a portion of the cooling circuit, each nozzle defined by a pressure side of a first guide vane, a suction side of the adjacent guide vane, an outer end wall defined by the outer shroud, and an inner end wall defined by the inner shroud;wherein forces created by a rotation of the turbine blade motivate the cooling fluid through the cooling circuit; andwherein the pre-swirler is configured to impart swirl to the cooling fluid drawn through the nozzles and to direct the swirled cooling fluid toward a base of the turbine blade. 2. The gas turbine engine of claim 1, wherein the inner shroud is formed as a monolithic body. 3. The gas turbine engine of claim 1, wherein the outer shroud is formed as a monolithic body. 4. The gas turbine engine of claim 1, wherein the inner end wall and outer end wall each comprise a valley disposed between the adjacent guide vanes. 5. The gas turbine engine of claim 4, wherein the valley is disposed downstream with respect to a vortex formed in the drawn cooling fluid by a leading edge of the first guide vane during the rotation of the turbine blades. 6. The gas turbine engine of claim 1, wherein the inner end wall and outer end wall each comprise a hump abutting the pressure side of the first guide vane. 7. The gas turbine engine of claim 6, wherein a peak of the hump is disposed at approximately one third of a length of a chord line of the first guide vane from a leading edge of the first guide vane. 8. The gas turbine engine of claim 1, the cooling circuit further comprising an air supply passage configured to supply the cooling fluid from the source of the ambient air to the pre-swirler. 9. The gas turbine engine of claim 8, further comprising a strut that supports the pre-swirler in which the air supply passage is disposed. 10. A gas turbine engine, comprising: an ambient-air cooling circuit comprising a cooling channel disposed in a turbine blade and in fluid communication with a source of ambient air that provides cooling fluid, wherein forces created by a rotation of the turbine blade motivate the cooling fluid through the cooling circuit, the improvement comprising:a pre-swirler, comprising: an inner shroud formed as a monolithic; an outer shroud formed as a monolith; and a plurality of guide vanes disposed in an annular array there between, the pre-swirler defining a plurality of nozzles defining part of the cooling circuit, each nozzle comprising: an outer end wall defined by the outer shroud between adjacent guide vanes; an inner end wall defined by the inner shroud between the adjacent guide vanes; and a pressure side and a suction side of the adjacent guide vanes,wherein the pre-swirler is configured to impart circumferential motion about a longitudinal axis of a rotor disc to the cooling fluid drawn through the nozzles and to direct the swirled cooling fluid toward a base of the turbine blade. 11. The gas turbine engine of claim 10, wherein the inner end wall and the outer end wall of each nozzle comprises a respective valley. 12. The gas turbine engine of claim 10, wherein the inner end wall and the outer end wall of each nozzle comprises a respective hump abutting the pressure side of a respective guide vane. 13. The gas turbine engine of claim 10, the cooling circuit further comprising an air supply passage configured to supply the cooling fluid from the source of the ambient air to the pre-swirler, wherein the air supply passage is disposed within a strut that supports the pre-swirler. 14. A gas turbine engine, comprising: an ambient-air cooling circuit comprising a cooling channel disposed in a turbine blade and in fluid communication with a source of ambient air that supplies cooling fluid: anda pre-swirler, comprising: an inner shroud;an outer shroud; anda plurality of guide vanes disposed between the inner shroud and the outer shroud;wherein the inner shroud, the outer shroud, and the plurality of guide vanes define an annular array of nozzles defining part of the ambient-air cooling circuit, each nozzle bounded by two adjacent guide vanes, an inner end wall of the outer shroud, and an outer end wall of the inner shroud;wherein the nozzles are configured to direct the cooling fluid traveling there through towards a plurality of cooling fluid inlets present in bases of adjacently disposed rotating blades, andwherein the nozzles impart circumferential motion to the cooling fluid flowing there through about an axis of rotation about which the rotating blades rotate. 15. The gas turbine engine of claim 14, wherein the inner shroud and the outer shroud are each formed as respective monolithic bodies. 16. The gas turbine engine of claim 14, wherein the inner end wall of the outer shroud and the outer end wall of the inner shroud of each nozzle comprises a respective valley. 17. The gas turbine engine of claim 14, wherein the inner end wall of the outer shroud and the outer end wall of the inner shroud of each nozzle comprises a respective hump abutting a pressure side of a respective guide vane. 18. The gas turbine engine of claim 14, the cooling circuit further comprising an air supply passage configured to supply the ambient air from the source of the ambient air to the pre-swirler, wherein the air supply passage is disposed within a strut that supports the pre-swirler.
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