Steam turbine inner shell assembly with common grooves
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-009/04
F01D-025/24
F01D-025/26
출원번호
US-0778404
(2013-02-27)
등록번호
US-9359913
(2016-06-07)
발명자
/ 주소
Montgomery, Michael Earl
Willett, Fred Thomas
출원인 / 주소
GENERAL ELECTRIC COMPANY
대리인 / 주소
Nixon & Vanderhye P.C.
인용정보
피인용 횟수 :
0인용 특허 :
54
초록▼
An inner shell assembly for a steam turbine includes an inner shell with a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves. Each of the nozzle carriers supports at least one nozzle and bucket for a turbine stage via a d
An inner shell assembly for a steam turbine includes an inner shell with a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves. Each of the nozzle carriers supports at least one nozzle and bucket for a turbine stage via a dovetail, where the inner shell, the plurality of nozzle carriers and the nozzles and buckets define a steam path. A radial position of the dovetails in the nozzle carriers within its corresponding grooves is selectable according to the steam path, and an axial width of each of the nozzle carriers is selectable according to the steam path.
대표청구항▼
1. An inner shell assembly of a steam turbine located radially inward of an outer shell of the steam turbine, the inner shell assembly comprising: an inner shell including a plurality of grooves of preset dimensions; anda plurality of nozzle carriers respectively securable in the plurality of groove
1. An inner shell assembly of a steam turbine located radially inward of an outer shell of the steam turbine, the inner shell assembly comprising: an inner shell including a plurality of grooves of preset dimensions; anda plurality of nozzle carriers respectively securable in the plurality of grooves, each of the nozzle carriers supporting at least one nozzle for a steam turbine stage via a dovetail, wherein the inner shell, the plurality of nozzle carriers and the nozzles define a steam path, and wherein a total axial and radial space available to accommodate the steam path is fixed by at least the inner shell and the plurality of grooves,wherein a radial position of the dovetails in the plurality of nozzle carriers within its corresponding plurality of grooves is variable within the total axial and radial space according to the steam path, and wherein an axial width of each of the plurality of nozzle carriers is selectable according to the steam path such that in one assembly with a first steam path in said inner shell, a first number of the nozzles is supported by the plurality of nozzle carriers, and in another assembly with a second steam path in said inner shell, a second number of the nozzles is supported by the plurality of nozzle carriers. 2. An inner shell assembly according to claim 1, wherein the preset dimensions are determined prior to defining the steam path. 3. An inner shell assembly according to claim 1, wherein axial widths of each the plurality of grooves are equivalent, and wherein radial depths of each of the plurality of grooves are equivalent. 4. An inner shell assembly according to claim 1, wherein the plurality of nozzle carriers and nozzles are positionable in the plurality of grooves and nozzle carriers, respectively, such that the plurality of nozzles can be arranged in configurations from substantially cylindrical to conical across a radial range of the plurality of nozzle carriers. 5. An inner shell assembly according to claim 1, wherein respective ones of the plurality of nozzle carriers are equally sized. 6. An inner shell assembly according to claim 1, wherein the plurality of nozzle carriers are sized differently to accommodate the steam path. 7. An inner shell assembly according to claim 1, wherein a steam path axial design flexibility is inversely proportional to a product of the number of grooves and an axial width of the grooves. 8. An inner shell assembly according to claim 1, further comprising at least one steam admission port or steam extraction port through the inner shell and through adjacent ones of the plurality of nozzle carriers. 9. An inner shell assembly according to claim 1, wherein the nozzle carriers are structurally configured to achieve a desired thermal response. 10. An inner shell assembly according to claim 9, wherein the structural configuration of the nozzle carriers to achieve the desired thermal response comprises areas of reduced mass. 11. An inner shell assembly according to claim 10, wherein the areas of reduced mass comprise at least one of appendages of the nozzle carriers and an outer portion of the nozzle carriers. 12. An inner shell assembly according to claim 9, wherein the structural configuration of the nozzle carriers to achieve the desired thermal response comprises nozzle carrier surfaces with increased heat transfer characteristics. 13. An inner shell assembly according to claim 12, wherein the nozzle carrier surfaces with increased heat transfer characteristics comprise at least one of a textured or dimpled surface and a finned surface. 14. A steam turbine comprising: an outer shell and an inner shell assembly defining a steam flow path;a rotor and a stator disposed in the steam flow path; anda plurality of stationary nozzles coupled with the stator that direct steam in the steam flow path into a plurality of rotatable buckets coupled with the rotor,wherein the inner shell assembly includes: an inner shell including a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves, each of the plurality of nozzle carriers supporting at least one nozzle for a turbine stage, wherein a total axial and radial space available to accommodate the steam flow path is fixed by the outer shell, the inner shell and the plurality of grooves,wherein a radial position of the nozzles within the plurality of nozzle carriers in the corresponding plurality of grooves is variable within the total axial and radial space according to the steam path, and wherein an axial width of each of the plurality of nozzle carriers is selectable according to the steam path such that in one assembly with a first steam path in said inner shell, a first number of the nozzles is supported by the plurality of nozzle carriers and in another assembly with a second steam path in said inner shell, a second number of the nozzles is supported by the plurality of nozzle carriers. 15. A steam turbine according to claim 14, wherein the preset dimensions are determined prior to defining the steam path. 16. A steam turbine according to claim 14, wherein axial widths of each the plurality of grooves are equivalent, and wherein radial depths of each of the plurality of grooves are equivalent. 17. A method of forming a steam path with an inner shell assembly in a steam turbine, the method comprising: forming a plurality of grooves of preset dimensions in an inner shell;respectively securing a plurality of nozzle carriers in the plurality of grooves, each of the plurality of nozzle carriers supporting at least one nozzle for a turbine stage, wherein the securing step is practiced by (1) selecting an axial width of each of the plurality of nozzle carriers according to the steam path, and (2) selecting a radial position of the at least one nozzle in the plurality of nozzle carriers in the corresponding plurality of grooves according to the steam path such that in one assembly with a first steam path in said inner shell, a first number of nozzles is supported by the plurality of nozzle carriers and in another assembly with a second steam path in said inner shell, a second number of the nozzles is supported by the plurality of nozzle carriers. 18. A method according to claim 17, wherein the forming step is practiced by determining the preset dimensions prior to defining the steam path. 19. A method according to claim 17, further comprising providing at least one steam admission port or steam extraction port through the inner shell and through adjacent ones of the plurality of nozzle carriers. 20. A method according to claim 17, further comprising tuning the nozzle carriers to achieve a desired thermal response. 21. A method according to claim 20, wherein the tuning step comprises reducing a mass of the nozzle carriers. 22. A method according to claim 21, wherein the reducing step comprises removing material from at least one of appendages of the nozzle carriers and an outer portion of the nozzle carriers. 23. A method according to claim 20, wherein the tuning step comprises providing surfaces of the nozzle carriers with increased heat transfer characteristics. 24. A method according to claim 23, wherein the providing step comprises providing at least one of a textured or dimpled surface and a finned surface.
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