Fluid flow machine especially gas turbine penetrated axially by a hot gas stream
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/12
F01D-005/08
F01D-011/00
F01D-011/02
출원번호
US-0912603
(2013-06-07)
등록번호
US-9657641
(2017-05-23)
우선권정보
RU-2010150605 (2010-12-09)
발명자
/ 주소
Khanin, Alexander Anatolievich
출원인 / 주소
General Electric Company
대리인 / 주소
Wilson, Charlotte C.
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
In a fluid flow machine, especially a gas turbine, axially penetrated by a hot gas stream, the rotor shaft is surrounded by heat shield segments or by base plates of the rotor blades on the rotor side. In the heat shield segments and in the base plates, cooling air chambers are provided, communicati
In a fluid flow machine, especially a gas turbine, axially penetrated by a hot gas stream, the rotor shaft is surrounded by heat shield segments or by base plates of the rotor blades on the rotor side. In the heat shield segments and in the base plates, cooling air chambers are provided, communicating with each other and with a cooling air source, which chambers communicate at least partially with gaps which extend in the longitudinal direction or peripheral direction of the rotor shaft between adjacent rotor blades or between heat shield segments and adjacent base plates of the rotor blades. These gaps are closed off by sealing bands such that a cooling air entry into the hot gas stream is only possible at the ends of the base plates of the rotor blades pointing contrary to the flow direction.
대표청구항▼
1. A fluid flow machine penetrated axially by a hot gas stream, the fluid flow machine comprising: a rotor shaft;rows of rotor blades, each rotor blade having a base segment attached to the rotor shaft, a base plate radially outward of the base segment, and an airfoil extending radially outward of t
1. A fluid flow machine penetrated axially by a hot gas stream, the fluid flow machine comprising: a rotor shaft;rows of rotor blades, each rotor blade having a base segment attached to the rotor shaft, a base plate radially outward of the base segment, and an airfoil extending radially outward of the base plate, wherein adjacent rotor blades in a respective row define therebetween a first gap;rows of guide vanes on a housing side, the guide vanes being arranged respectively axially between successive rows of rotor blades;heat shield segments attached to the rotor shaft opposite ends of the guide vanes, the heat shield segments being located between the base segments, wherein a second gap is defined between respective ones of the heat shield segments and respective ones of the adjacent base segments;wherein first cooling air chambers are formed along the rotor shaft inside the heat shield segments and base segments, the first cooling air chambers communicating with each other and with a cooling air source;wherein second cooling air chambers are arranged radially outward of the first cooling air chambers inside the base plates between the rotor blades;wherein each of the base plates defines, along a side surface thereof, a first axial groove and a second oblique groove, the second oblique groove being oblique to a radial plane of the rotor shaft; andwherein a first sealing band is inserted in the first axial groove and a second sealing band is inserted in the second oblique groove in a radially inwardly oriented position, such that the second cooling air chambers are able to be vented into the hot gas stream exclusively at their ends situated upstream with respect to the direction of the hot gas stream. 2. A fluid flow machine according to claim 1, further comprising third sealing bands positioned between adjacent base segments in the axial direction of the rotor shaft. 3. A fluid flow machine according to claim 2, wherein each of the base plates defines, along the side surface thereof, a third groove parallel to the first axial groove; and wherein the third sealing bands are inserted in the third grooves. 4. A fluid flow machine according to claim 2, further comprising fourth sealing bands provided in a fourth groove in an end face of the rotor blade between the base segment and the base plate. 5. A fluid flow machine according to claim 4, wherein each of third sealing bands and each of the fourth sealing bands are connected with each other in a T-shape. 6. A fluid flow machine according to claim 2, wherein each of the second sealing bands has an end proximate to the rotor shaft, the end being accessible at downstream end faces of the base plates. 7. A fluid flow machine according to claim 6, wherein the ends of the second sealing bands proximate to the rotor shaft are bent to form concave sides, the concave sides cooperating with correspondingly convex stops on the base plates.
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이 특허에 인용된 특허 (5)
Brown David L. (Medfield MA) McLaurin Leroy D. (Springfield PA), Cooled combustion turbine blade with retrofit blade seal.
Hendley David G. (Wyoming OH) Fledderjohn Steve R. (West Chester OH) Bauer Randall C. (Hamilton OH) Clarke Jonathon P. (West Chester OH) Webb Alan L. (Mason OH), Rotor disk post cooling system.
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