Casing of a gas turbine engine having a radial spoke with a flow guiding element
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/20
F03B-001/00
F03D-005/00
출원번호
US-0524766
(2008-01-25)
등록번호
US-8402769
(2013-03-26)
우선권정보
EP-07001910 (2007-01-29)
국제출원번호
PCT/EP2008/050867
(2008-01-25)
§371/§102 date
20090728
(20090728)
국제공개번호
WO2008/092806
(2008-08-07)
발명자
/ 주소
Maltson, John David
출원인 / 주소
Siemens Aktiengesellschaft
인용정보
피인용 횟수 :
2인용 특허 :
5
초록▼
A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least
A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.
대표청구항▼
1. A section of a gas turbine engine, the casing surrounding a combustor and comprising: a casing, surrounding the combustor and comprising: a radial spoke, the radial spoke includes an aerodynamic shape and comprises: an upstream leading side,a downstream trailing side,a first side,a second side op
1. A section of a gas turbine engine, the casing surrounding a combustor and comprising: a casing, surrounding the combustor and comprising: a radial spoke, the radial spoke includes an aerodynamic shape and comprises: an upstream leading side,a downstream trailing side,a first side,a second side opposite to the first side, anda flow guiding element arranged on at least the first side,wherein the radial spoke is used as a support for a carrier ring of a turbine guide vane ring, whereby cooling air exiting a compressor diffuser flows between the spoke and a transition duct of the combustor,wherein the first side and the second side extend from the upstream leading side to the downstream trailing side, andwherein the flow guiding element is formed is such a way that a flow of cooling air exiting the compressor diffuser is deflected and turned circumferentially about the axis of the gas turbine engine, and wherein at least a portion of the downstream trailing side comprises a concave surface in the form of a chute that extends in the circumferential direction about the axis of the gas turbine engine. 2. The section as claimed in claim 1, wherein the radial spoke extends along a radial axis, andwherein the flow guiding element is arranged in a central circumferential area relative to the radial axis. 3. The section as claimed in claim 1, wherein the flow guiding element extends to the trailing side of the radial spoke. 4. The section as claimed in claim 1, wherein a plurality of flow guiding elements are arranged on the first side and the second side of the radial spoke. 5. The section as claimed in claim 1, wherein the flow guiding element comprises a metal. 6. The section as claimed in claim 5, wherein the flow guiding element comprises a sheet metal. 7. The section as claimed in claim 1, wherein the flow guiding element comprises a ceramic material. 8. The section as claimed in claim 1, wherein the flow guiding element comprises a plurality of filaments of carbon or Kevlar fibres. 9. The section as claimed in claim 1, wherein the flow guiding element is welded onto the spoke. 10. The section as claimed in claim 1, wherein the flow guiding element is brazed onto the spoke. 11. The section as claimed in claim 1, wherein the spoke and the flow guiding element are cast in one piece. 12. The section as claimed in claim 1, wherein the flow guiding element is an aerodynamic vane, extending to the downstream trailing side of the radial spoke, andwherein the aerodynamic vane is bent to redirect the flow of cooling air. 13. The section as claimed in claim 1, wherein the aerodynamic vane has a first surface and a second surface,wherein the first surface includes an upstream leading edge region and the second surface includes a downstream trailing edge region, andwherein the first surface is inclined relative to the second surface. 14. The section as claimed in claim 13, wherein a bending angle between the leading edge region and the trailing edge region is in a range between 120° and 170°. 15. The section as claimed in claim 14, wherein the bending angle is 150°. 16. The section as claimed in claim 1, wherein an angle of attack of the flow guiding element, relative to a cooling air streaming along the radial spoke, is adjustable, andwherein the cooling air exits the compressor diffuser. 17. A gas turbine engine, comprising: a section, comprising: a casing, surrounding the combustor and comprising: a radial spoke, the radial spoke includes an aerodynamic shape and comprises: an upstream leading side,a downstream trailing side,a first side,a second side opposite to the first side, anda flow guiding element arranged on at least the first side,wherein the radial spoke is used as a support for a carrier ring of a turbine guide vane ring, whereby cooling air exiting a compressor diffuser flows between the spoke and a transition duct of the combustor,wherein the first side and the second side extend from the upstream leading side to the downstream trailing side, andwherein the flow guiding element is formed is such a way that a flow of cooling air exiting the compressor diffuser is deflected and turned circumferentially about the axis of the gas turbine engine, and wherein at least a portion of the downstream trailing side comprises a concave surface in the form of a chute that extends in the circumferential direction about the axis of the gas turbine engine. 18. The gas turbine engine as claimed in claim 17, wherein the radial spoke extends along a radial axis, andwherein the flow guiding element is arranged in a central circumferential area relative to the radial axis.
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이 특허에 인용된 특허 (5)
Sato Isao (Hitachi JPX) Kato Fumio (Hitachi JPX) Uchiyama Yoshihiro (Hitachi JPX) Iizuka Nobuyuki (Hitachi JPX) Hata Tsuneyuki (Hitachi JPX), Combustor of gas turbine with features for vibration reduction and increased cooling.
Alary Jean-Paul D. (Saint Maur des Fosses FRX) Barbier Gerard Y. G. (Morangis FRX) Delahaye Corine G. (Mormant FRX) Havard Jacques G. W. R. (Moissy Cramayel FRX) Mackovic Paul (Villiers S/Marne FRX) , Gas turbine engine having an integral guide vane and separator diffuser.
Birch Stanley F. (Bellevue Federal Way WA) Lawler John A. (Federal Way WA) Paynter Gerald C. (Seattle WA), Vortex generators for internal mixing in a turbofan engine.
Subramaniyan, Moorthi; Chengappa, Manjunath Bangalore; Patel, Pradeep, Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same.
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