IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0512559
(2006-08-29)
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등록번호 |
US-7717672
(2010-06-10)
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발명자
/ 주소 |
- Barton, Michael T.
- Kington, Harry L.
- Palmer, Donald L.
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출원인 / 주소 |
- Honeywell International Inc.
|
대리인 / 주소 |
Ingrassia Fisher & Lorenz, P.C.
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인용정보 |
피인용 횟수 :
2 인용 특허 :
9 |
초록
▼
A radial diffuser comprises a housing, a plurality of diffuser vanes, and a plurality of integral service vanes. The housing includes an air inlet and an air outlet, and defines a radial section extending radially outward from the air inlet, an axial section extending axially to the air outlet, and
A radial diffuser comprises a housing, a plurality of diffuser vanes, and a plurality of integral service vanes. The housing includes an air inlet and an air outlet, and defines a radial section extending radially outward from the air inlet, an axial section extending axially to the air outlet, and a transition including a bend and extending between the radial and axial sections. The diffuser vanes are coupled to the housing, and are disposed in, and define diffusion flow passages. The integral service vanes are coupled to the housing, extend around the bend, and define transition flow passages, each in fluid communication with at least one diffusion flow passage. At least some of the integral service vanes include a service passage extending therethrough and configured to allow a service conduit to extend therethrough without crossing either a diffusion flow passage or a transition flow passage.
대표청구항
▼
We claim: 1. A radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising: a housing including an air inlet and an air outlet, and defining a radial section, an axial section, and a transition b
We claim: 1. A radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising: a housing including an air inlet and an air outlet, and defining a radial section, an axial section, and a transition between the air inlet and air outlet, the radial section extending at least substantially radially outward from the air inlet to the transition, the axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section; a plurality of diffuser vanes coupled to the housing and extending through the radial section and the transition, each of the plurality of diffuser vanes defining a diffusion flow passage through the radial section and a transition flow passage through the transition, the transition flow passage in fluid communication with the diffusion flow passage, at least one of the plurality of diffuser vanes including a service passage extending therethrough, the service passage configured to allow a service conduit to extend therethrough without crossing either the diffusion flow passage or the transition flow passage. 2. The radial diffuser of claim 1, wherein: the bend provides an at least substantially continuous turn between the radial section and the axial section. 3. The radial diffuser of claim 1, wherein: each of the plurality of diffuser vanes has a first vane component defining the diffusion flow passage and a second vane component defining the transition flow passage; and the second vane component has a thickness that is greater than a thickness of the first vane component. 4. The radial diffuser of claim 1, wherein: the first vane component is made at least in part from a first material; the second vane component is made at least in part from a second material; and the second material is lighter than the first material. 5. The radial diffuser of claim 4, wherein: the first material is steel. 6. The radial diffuser of claim 4, wherein: the second material is selected from the group consisting of titanium, aluminum, and plastic. 7. The radial diffuser of claim 1, wherein each of the plurality of diffuser vanes is also configured to deswirl the diffused air. 8. The radial diffuser of claim 1, farther comprising: one or more service conduits extending through the service passage. 9. The radial diffuser of claim 8, wherein: the one or more service conduits are made of metal tubing. 10. The radial diffuser of claim 1, wherein: the service passage is further configured to allow a structural tie with one or more external structures. 11. A gas turbine engine, comprising: an engine housing; a compressor, a combustor, and a turbine all mounted in flow series within the housing, the compressor including at least: a compressor housing; an impeller rotationally mounted within the compressor housing and having a leading edge and a trailing edge, the impeller operable, upon rotation thereof, to discharge a flow of air having a velocity magnitude and a pressure magnitude from the trailing edge; and a radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising: a diffuser housing including an air inlet and an air outlet, and defining a radial section, an axial section, and a transition between the air inlet and air outlet, the air inlet in fluid communication with the impeller trailing edge to thereby receive the flow of air discharged therefrom, the radial section extending at least substantially radially outward from the air inlet to the transition, the axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section; a plurality of diffuser vanes coupled to the diffuser housing and extending through the radial section and the transition, each of the plurality of diffuser vanes defining a diffusion flow passage through the radial section and a transition flow passage through the transition, the transition flow passage in fluid communication with the diffusion flow passage, at least one of the plurality of diffuser vanes including a service passage extending therethrough, the service passage configured to allow a service conduit to extend therethrough without crossing either the diffusion flow passage or the transition flow passage. 12. The gas turbine engine of claim 11, wherein: each of the plurality of diffuser vanes has a first vane component defining the diffusion flow passage and a second vane component defining the transition flow passage; and the second vane component has a thickness that is greater than a thickness of the first vane component. 13. The gas turbine engine of claim 11, wherein: the first vane component is made at least in part from a first material; the second vane component is made at least in part from a second material; and the second material is lighter than the first material. 14. The gas turbine engine of claim 11, -wherein each of the plurality of diffuser vanes is also configured to deswirl the diffused air. 15. A diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the diffuser comprising: a housing including an air inlet and an air outlet, and defining a radial section, an axial section, and a transition between the air inlet and air outlet, the radial section extending at least substantially radially outward from the air inlet to the transition, the axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section; a plurality of diffuser vanes coupled to the housing and extending through the radial section, the transition, and the axial section, each of the plurality of diffuser vanes defining a diffusion flow passage through the radial section and a deswirl flow passage through the axial section, wherein air is diffused in the diffusion flow passage and is deswirled in the deswirl flow passage of the same diffuser vane, at least one of the plurality of diffuser vanes including a service passage extending therethrough, the service passage configured to allow a service conduit to extend therethrough without crossing the diffusion flow passage. 16. The diffuser of claim 15, wherein the bend provides an at least substantially continuous turn between the radial section and the axial section. 17. The diffuser of claim 15, wherein each of the plurality of diffuser vanes further defines a transition flow passage through the transition, the transition flow passage in fluid communication with the diffusion flow passage and the deswirl flow passage. 18. The diffuser of claim 17, wherein: each of the plurality of diffuser vanes has a first vane component defining the diffusion flow passage, a second vane component defining the transition flow passage, and a third vane component comprising the deswirl flow passage. 19. The diffuser of claim 18, wherein the second vane component has a thickness that is greater than a thickness of the first vane component. 20. The diffuser of claim 18, further comprising: one or more service conduits extending through the service passage.
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