Axial compressor and method for controlling stage-to-stage leakage therein
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-011/00
F01D-005/30
F01D-005/08
출원번호
US-0834745
(2013-03-15)
등록번호
US-9470098
(2016-10-18)
발명자
/ 주소
Latimer, Jeremy Peter
Bonini, Eric Richard
Duong, John
출원인 / 주소
General Electric Company
대리인 / 주소
Sutherland Asbill & Brennan LLP
인용정보
피인용 횟수 :
0인용 특허 :
12
초록▼
The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor. The rotor disk may include a slot defined about a radially outer surface of the rotor disk, and the slot may incl
The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor. The rotor disk may include a slot defined about a radially outer surface of the rotor disk, and the slot may include a slot planar surface facing away from the rotor disk. The compressor also may include a compressor blade coupled to the rotor disk via the slot. The compressor blade may include a platform positioned over the radially outer surface of the rotor disk, and the platform may include a platform sealing edge facing toward the rotor disk. The compressor further may include a gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low-pressure side of the compressor blade. The present application and the resultant patent further provide a related method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine.
대표청구항▼
1. An axial compressor for a gas turbine engine, the compressor comprising: a rotor disk positioned along a length of a longitudinal axis of the compressor, wherein the rotor disk comprises a slot defined about a radially outer surface of the rotor disk and extending from an upstream end of the roto
1. An axial compressor for a gas turbine engine, the compressor comprising: a rotor disk positioned along a length of a longitudinal axis of the compressor, wherein the rotor disk comprises a slot defined about a radially outer surface of the rotor disk and extending from an upstream end of the rotor disk to a downstream end of the rotor disk, and wherein the slot comprises a slot planar surface facing radially outward from the rotor disk;a compressor blade coupled to the rotor disk via the slot, wherein the compressor blade comprises a platform positioned over the radially outer surface of the rotor disk, wherein the platform comprises a platform sealing edge facing toward the rotor disk, wherein the platform sealing edge is parallel to the slot planar surface, and wherein the platform sealing edge and the slot planar surface are angled radially inward; anda gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low pressure side of the compressor blade. 2. The axial compressor of claim 1, wherein the platform sealing edge is positioned closer to an upstream end of the platform than a downstream end of the platform, and wherein the slot planar surface is positioned closer to an upstream end of the slot than a downstream end of the slot. 3. The axial compressor of claim 1, wherein the platform further comprises a platform planar surface and a platform curved surface each facing toward the rotor disk, wherein the platform planar surface extends from an upstream end of the platform to the platform sealing edge, and wherein the platform curved surface extends from the platform sealing edge to a downstream end of the platform. 4. The axial compressor of claim 1, wherein the slot comprises a mouth defined about the radially outer surface of the rotor disk and extending from the upstream end of the rotor disk to the downstream end of the rotor disk, and wherein the slot planar surface is positioned on the mouth. 5. The axial compressor of claim 1, wherein the slot extends axially from the upstream end of the rotor disk to the downstream end of the rotor disk. 6. The axial compressor of claim 1, wherein the slot extends obliquely from the upstream end of the rotor disk to the downstream end of the rotor disk. 7. The axial compressor of claim 1, wherein the platform comprises a full-pitch platform comprising lateral surfaces configured to abut lateral surfaces of platforms of adjacent compressor blades. 8. The axial compressor of claim 1, wherein a magnitude of the gap is constant between the platform sealing edge and the slot planar surface. 9. The axial compressor of claim 2, wherein the platform comprises a first lateral surface and a second lateral surface each extending between the upstream end and the downstream end of the platform, wherein the platform sealing edge extends from one of the first lateral surface and the second lateral surface of the platform to a root of the compressor blade, and wherein the slot planar surface extends from the upstream end of the slot toward the downstream end of the slot. 10. A method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine, the method comprising: passing a flow of compressed air over a compressor blade from a low-pressure side of the compressor blade to a high-pressure side of the compressor blade;passing a flow of leakage air between a platform of the compressor blade and a rotor disk from the high-pressure side of the compressor blade to the low-pressure side of the compressor blade; andcontrolling the flow of leakage air with a gap defined between a platform sealing edge of the platform and a slot planar surface of a slot defined about a radially outer surface of the rotor disk, wherein the slot extends from an upstream end of the rotor disk to a downstream end of the rotor disk, and wherein the gap is positioned closer to the low-pressure side of the compressor blade than the high-pressure side of the compressor blade. 11. The method of claim 10, further comprising minimizing a magnitude of the gap to minimize the flow of leakage air, wherein the magnitude of the gap is constant between the platform sealing edge and the slot planar surface. 12. An axial compressor for a gas turbine engine, the compressor comprising: a rotor disk positioned along a length of a longitudinal axis of the compressor, wherein the rotor disk comprises a slot defined about a radially outer surface of the rotor disk and extending from an upstream end of the rotor disk to a downstream end of the rotor disk, and wherein the slot comprises a first slot planar surface and a second slot planar surface each facing radially outward from the rotor disk;a compressor blade coupled to the rotor disk via the slot, wherein the compressor blade comprises a platform positioned over the radially outer surface of the rotor disk, and wherein the platform comprises a first platform sealing edge and a second platform sealing edge each facing toward the rotor disk and positioned closer to an upstream end of the platform than a downstream end of the platform, and wherein the platform comprises a full-pitch platform comprising lateral surfaces configured to abut lateral surfaces of platforms of adjacent compressor blades;a first gap defined between the first platform sealing edge and the first slot planar surface; anda second gap defined between the second platform sealing edge and the second slot planar surface;wherein the first gap and the second gap each are configured to control a leakage flow of air from a high-pressure side of the compressor blade to a low pressure side of the compressor blade. 13. The axial compressor of claim 12, wherein the first platform sealing edge is parallel to the first slot planar surface, and wherein the second platform sealing edge is parallel to the second slot planar surface. 14. The axial compressor of claim 12, wherein the first slot planar surface and the second slot planar surface are positioned closer to an upstream end of the slot than a downstream end of the slot. 15. The axial compressor of claim 12 wherein the slot comprises a mouth defined about the radially outer surface of the rotor disk and extending from the upstream end of the rotor disk to the downstream end of the rotor disk, and wherein the first slot planar surface and the second slot planar surface are positioned on the mouth. 16. The axial compressor of claim 12, wherein the compressor blade comprises a root extending radially inward from the platform, and wherein the root is positioned circumferentially between the first platform sealing edge and the second platform sealing edge. 17. The axial compressor of claim 12, wherein the first platform sealing edge is positioned on a concave side of the compressor blade, and wherein the second platform sealing edge is positioned on a convex side of the compressor blade.
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