Arrangement for axially and radially fixing the guide vanes of a vane ring of a gas turbine
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0515597
(2003-05-15)
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등록번호 |
US-7396206
(2008-07-08)
|
우선권정보 |
DE-102 23 655(2002-05-28) |
국제출원번호 |
PCT/DE03/001568
(2003-05-15)
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§371/§102 date |
20050620
(20050620)
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국제공개번호 |
WO03/102379
(2003-12-11)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
4 인용 특허 :
7 |
초록
▼
A gas turbine has at least one guide blade ring, whose guide vanes are axially and radially fixed via detachable locking elements. A shell ring is configured as a freely machinable component having projections bearing a stop surface and mating surfaces. A holding piece is provided for each guide van
A gas turbine has at least one guide blade ring, whose guide vanes are axially and radially fixed via detachable locking elements. A shell ring is configured as a freely machinable component having projections bearing a stop surface and mating surfaces. A holding piece is provided for each guide vane, which engages into corresponding recesses on an upstream shell ring. The holding pieces are held in a position determined by the locking elements, via spring clips.
대표청구항
▼
The invention claimed is: 1. In a gas turbine having a turbine housing, and guide vane rings and moving blade rows arranged axially side by side, an arrangement for axially and radially fixing guide vanes of the guide vane ring wherein stop surfaces of the guide vanes that serve for fixation are he
The invention claimed is: 1. In a gas turbine having a turbine housing, and guide vane rings and moving blade rows arranged axially side by side, an arrangement for axially and radially fixing guide vanes of the guide vane ring wherein stop surfaces of the guide vanes that serve for fixation are held in place by locking elements, which are structurally separate from the turbine housing; wherein: the locking elements are assigned to radially outer ends of the guide vanes farthest from a hub of the turbine; said locking elements engage in a form-fitting manner with each other; and said locking elements comprise shell rings having respectively two axial stop surfaces, holding pieces that engage into respective corresponding recesses of the shell rings, and spring clips that engage with inner surfaces of said shell rings and with support surfaces of said holding pieces, and retain said holding pieces in said recesses of said shell rings. 2. The arrangement of claim 1, wherein radial and circumferential mating surfaces of the shell ring are arranged on radial projections, to which are assigned corresponding contact surfaces on the outer radial ends of the guide vanes. 3. The apparatus according to claim 1, wherein said shell rings collectively form an enclosure that bounds a gas flow path of said turbine. 4. The apparatus according to claim 3, wherein said locking elements comprise an axially extending portion of each said shell ring which portion is configured to engage with radial projections on an adjacent shell ring. 5. The apparatus according to claim 4, wherein said holding pieces comprise substantially U-shaped members having arms that engage in corresponding recesses in said axially extending portions of said shell rings. 6. The apparatus according to claim 5, wherein said spring clips engage with inward surfaces of said axially extending portion and said support surfaces of said holding pieces. 7. The apparatus according to claim 5, wherein said spring clips engage with inward surfaces of said axially extending portion and said support surfaces of said holding pieces. 8. The apparatus according to claim 4, wherein said holding pieces comprise substantially U-shaped members having arms that engage in corresponding recesses in said axially extending portions of said shell rings. 9. In a gas turbine having a turbine housing, and guide vane rings and moving blade rows arranged axially side by side, an arrangement for axially and radially fixing guide vanes of the guide vane ring wherein stop surfaces of the guide vanes that serve for fixation are arranged on locking elements, which are structurally separate from the turbine housing; wherein: the locking elements are assigned to radially outer ends of the guide vanes farthest from a hub of the turbine; said locking elements engage in a form-fitting manner with each other; and said locking elements comprise shell rings having respectively two axial stop surfaces and holding pieces, which engage into respective corresponding recesses of the shell rings and serve as support surface for a spring clip; radial and circumferential mating surfaces of the shell ring are arranged on radial projections, to which are assigned corresponding contact surfaces on the outer radial ends of the guide vanes; spring clips engage on the support surfaces of the holding pieces; and corresponding bearing surfaces on the shell ring are assigned to the spring clips to detachably fix the holding pieces. 10. A gas turbine, comprising: a turbine housing; guide vane rings and moving blade rows arranged alternately in axial sequence within said housing; fixing means for axially and radially fixing guide vanes of the guide vane ring within said housing; wherein, said fixing means comprise stop surfaces of the guide vanes; said stop surfaces are provided on locking elements that are structurally separate from the turbine housing; the locking elements are assigned to radially outer ends of the guide vanes farthest from a hub of the turbine; said locking elements engage in a form-fitting manner with each other; and said locking elements comprise shell rings having respectively two axial stop surfaces, holding piece that engage into respective corresponding recesses of the shell rings, and spring clips that engage with inner surfaces of said shell rings and with support surfaces of said holding pieces, and retain said holding pieces in said recesses of said shell rings. 11. The arrangement of claim 10, wherein radial and circumferential mating surfaces of the shell ring are arranged on radial projections, to which are assigned corresponding contact surfaces on the outer radial ends of the guide vanes. 12. The apparatus according to claim 10, wherein said shell rings collectively form an enclosure that bounds a gas flow path of said turbine. 13. The apparatus according to claim 12, wherein said locking elements comprise an axially extending portion of each said shell ring which portion is configured to engage with radial projections on an adjacent shell ring. 14. A gas turbine, comprising: a turbine housing; guide vane rings and moving blade rows arranged alternately in axial sequence within said housing; fixing means for axially and radially fixing guide vanes of the guide vane ring within said housing; wherein, said fixing means comprise stop surfaces of the guide vanes; said stop surfaces are provided on locking elements that are structurally separate from the turbine housing; the locking elements are assigned to radially outer ends of the guide vanes farthest from a hub of the turbine; said locking elements engage in a form-fitting manner with each other; said locking elements comprise shell rings having respectively two axial stop surfaces and holding pieces which engage into respective corresponding recesses of the shell rings; radial and circumferential mating surfaces of the shell ring are arranged on radial projections, to which are assigned corresponding contact surfaces on the outer radial ends of the guide vanes; spring clips engage on the support surfaces of the holding pieces; and corresponding bearing surfaces on the shell ring are assigned to the spring clips to detachably fix the holding pieces.
이 특허에 인용된 특허 (7)
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Wilkinson Wilfred H. (Turnditch GBX), A nozzle guide vane structure for a gas turbine engine.
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Sweeney Derek J. (Dublin IEX), Low-pressure turbine heat shield.
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Ayache Michel R. (Epinay sous Senart FRX) Glowacki Pierre A. (Melun FRX) Mandet Gerard M. F. (Epinay sous Senart FRX), Temperature control device for gas turbines.
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Brown Henry B. (Manchester CT) Cantor Eugene (Glastonbury CT) DeTolla Francis L. (Vernon CT) Vollinger Gary J. (Simsbury CT), Turbine cooling.
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Ross Steven A. ; Albers Robert J. ; Brill Edward P. ; Kemp Andrew D. ; Plemmons Larry W., Turbine nozzle assembly.
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Boyd Gary L. (Alpine CA) Shaffer James E. (Maitland FL), Turbine nozzle/nozzle support structure.
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Marey Daniel J. (Soisy Sur Seine FRX) Niclot Thierry J. M. (Chilly Mazarin FRX) Orsini Jean-Jacques R. A. (Viry Chatillon FRX), Vane extremity locking system.
이 특허를 인용한 특허 (4)
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Duong, Loc Quang; Hu, Xiaolan, Inlet guide vane drive system with spring preload on mechanical linkage.
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Hudson, Michael Thomas; Sech, John Robert, Load pin for compressor square base stator and method of use.
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Sluyter, Gregory Kent; Sener, Alexander Martin; Dziech, Aaron Michael, Shroud retention system with keyed retention clips.
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Sener, Alexander Martin, Shroud retention system with retention springs.
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