[특허]Conical helical of spiral combustor scroll device in gas turbine engine

Honeywell International, Inc.

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특허 상세정보

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Conical helical of spiral combustor scroll device in gas turbine engine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-001/00 F02G-003/00
미국특허분류(USC)	060/722; 060/752; 060/804; 060/805; 415/205
출원번호	US-0386771 (2003-03-11)
발명자 / 주소	Nguyen,Ly D. Aksoy,Hakan Kujala,Stony Frost,Cristopher
출원인 / 주소	Honeywell International, Inc.
인용정보	피인용 횟수 : 1 인용 특허 : 14

초록
▼

A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.

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We claim: 1. A turbine scroll of a turbine engine comprising: a combustion exhaust inlet; a combustion exhaust product discharge area defining a B-width; and an axial shift region providing a portion of said turbine scroll to have a irregular cross-sectional area centroid passing beyond said B-width; wherein said turbine scroll has a helical configuration. 2. A turbine scroll of a turbine engine comprising: a combustion exhaust inlet; a combustion exhaust product discharge area defining a B-width; and an axial shift region providing a portion of said turbine scroll to have a irregular cross-sectional area centroid passing beyond said B-width; wherein said turbine scroll has a helical configuration and wherein said irregular cross-sectional area has a flat curve portion curving around said helical configuration. 3. The turbine scroll of claim 2, wherein said combustion exhaust inlet is at the same azimuthal angle along said helical configuration as said combustion exhaust product discharge area. 4. The turbine scroll of claim 2, wherein said turbine scroll has a conical shape with a cross-sectional area decreasing from said combustion exhaust inlet to said combustion exhaust product discharge area. 5. The turbine scroll of claim 4, wherein said combustion exhaust inlet is at the same radial angle along said helical configuration as said combustion exhaust product discharge region. 6. The turbine scroll of claim 2, wherein said turbine scroll is attached to a combustor liner of said turbine engine. 7. The turbine scroll of claim 2, further comprising a joining line, said joining line being located along an outer perimeter of said turbine scroll. 8. The turbine scroll of claim 2, wherein said turbine engine is an engine of an aircraft. 9. The turbine scroll of claim 2 wherein said B-width is axially shifted. 10. A turbine scroll of a turbine engine comprising: a combustion exhaust inlet; a combustion exhaust product discharge area defining a B-width; and an axial shift region providing a portion of said turbine scroll to have an irregular cross-sectional area centroid passing beyond said B-width; wherein said turbine scroll has a helical configuration; said turbine scroll has a conical shape with a cross-sectional area decreasing from said combustion exhaust inlet to said combustion exhaust product discharge area; and said irregular cross-sectional area has a flat curve portion curving around said helical configuration. 11. The turbine scroll of claim 10, wherein said combustion exhaust inlet is at the same azimuthal angle along said helical configuration as said combustion exhaust product discharge area. 12. The turbine scroll of claim 10, wherein said turbine scroll is attached to a combustor liner of said turbine engine, said turbine engine being a turbine engine of an aircraft. 13. The turbine scroll of claim 10 wherein said B-width is axially shifted. 14. A turbine engine comprising a turbine scroll having a combustion exhaust inlet; a combustion exhaust product area defining a B-width; and an axial shift region providing a portion of said turbine scroll to have a cross-sectional area centroid passing beyond said B-width, wherein said combustion scroll has a helical configuration. 15. A turbine engine comprising a turbine scroll having a combustion exhaust inlet; a combustion exhaust product area defining a B-width; and an axial shift region providing a portion of said turbine scroll to have a cross-sectional area centroid passing beyond said B-width, wherein said combustion scroll has a helical configuration; said turbine scroll has a conical shape with a cross-sectional area decreasing from said combustion exhaust inlet to said combustion exhaust product discharge area; and said cross-sectional area has a flat curve portion curving around said helical configuration. 16. The turbine engine of claim 15, wherein said combustion exhaust inlet is at the same azimuthal angle along said helical configuration as said combustion exhaust product discharge area. 17. The turbine scroll of claim 15 wherein said B-width is axially shifted. 18. A turbine engine comprising a turbine scroll having a combustion exhaust inlet; a combustion exhaust product area defining a B-width; and an axial shift region providing a portion of said turbine scroll to have a cross-sectional area centroid passing beyond said B-width, wherein said combustion scroll has a helical configuration; a combustor housing, said combustor housing forming a cavity containing said turbine scroll, wherein said axial shift region occupies a previously empty space in said cavity. 19. A turbine engine comprising a turbine scroll having a combustion exhaust inlet; a combustion exhaust product area defining a B-width; and an axial shift region providing a portion of said turbine scroll to have a cross-sectional area centroid passing beyond said B-width, wherein said combustion scroll has a helical configuration; wherein said turbine scroll is attached to a combustor liner of said turbine engine, said turbine engine being a turbine engine of an aircraft. 20. A turbine engine comprising a turbine scroll having a combustion exhaust inlet, a combustion exhaust product discharge area defining a B-width, and an axial shift region providing a portion of said turbine scroll to have an irregular cross-sectional area centroid passing beyond said B-width, wherein said turbine scroll has a helical configuration; said turbine scroll has a substantially conical shape with a cross-sectional area decreasing from said combustion exhaust inlet to said combustion exhaust product discharge area; and said irregular cross-sectional area has a flat curve portion curving around said helical configuration. 21. The turbine engine of claim 20, wherein: said combustion exhaust inlet is at the same azimuthal angle along said helical configuration as said combustion exhaust product discharge area; and said turbine engine is a turbine engine of an aircraft. 22. The turbine scroll of claim 20 wherein said B-width is axially shifted. 23. A method for making a turbine engine comprising: attaching a first, combustion exhaust inlet end of a turbine scroll to a combustor liner of said turbine engine; attaching a second, opposite end of said turbine scroll to a combustion exhaust product discharge area defining a B-width; providing an axial shift region in said turbine scroll, said axial shift region resulting in a portion of said turbine scroll having an irregular cross-sectional area centroid passing beyond said B-width; and shaping said turbine scroll in a helical configuration. 24. A method for making a turbine engine comprising: attaching a first, combustion exhaust inlet end of a turbine scroll to a combustor liner of said turbine engine; attaching a second, opposite end of said turbine scroll to a combustion exhaust product discharge area defining a B-width; providing an axial shift region in said turbine scroll, said axial shift region resulting in a portion of said turbine scroll having an irregular cross-sectional area centroid passing beyond said B-width; and shaping said turbine scroll in a helical configuration; and forming said irregular cross-sectional area with a flat curve portion curving around said helical configuration. 25. The method for making a turbine engine of claim 24, further comprising shaping said turbine scroll has a conical shape with a cross-sectional area decreasing from said combustion exhaust inlet to said combustion exhaust product discharge area. 26. The method for making a turbine engine of claim 25, further comprising locating said combustion exhaust inlet at the same azimuthal angle along said helical configuration as said combustion exhaust product discharge area. 27. The method for making a turbine engine of claim 24, further comprising: providing a combustor housing to form a cavity containing said turbine scroll; and locating said axial shift region in a space in said cavity that was previously unoccupied, thereby requiring no additional increase in size of said cavity to accommodate said turbine scroll having said axial shift region. 28. The method for making a turbine engine of claim 24 wherein said B-width is axially shifted.

이 특허에 인용된 특허 (14)

이 특허를 인용한 특허 피인용횟수: 1

Schumacher, Jurgen C.; Critchley, Ian L.; Walhood, David G.; Kujala, Stony W.; Woodcock, Gregory O.. Transition scrolls for use in turbine engine assemblies. USP2012038127552.

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Conical helical of spiral combustor scroll device in gas turbine engine

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Conical helical of spiral combustor scroll device in gas turbine engine

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이 특허에 인용된 특허 (14)

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