Modular turbine airfoil and platform assembly with independent root teeth
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/30
출원번호
US-0793935
(2010-06-04)
등록번호
US-8496443
(2013-07-30)
발명자
/ 주소
Campbell, Christian X.
Davies, Daniel O.
Eng, Darryl
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
6인용 특허 :
12
초록▼
A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second po
A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second portion of the shank (29) that extends below the platform (30E-H) to engage other slots (52) in the disk. Thus the platform (30E-H) and the shank (23E-H) independently support their own centrifugal loads via their respective teeth. The platform may be formed in two portions (32E-H, 34E-H), that are bonded to each other at matching end-walls (37) and/or via pins (36G) passing through the shank (23E-H). Coolant channels (41, 43) may pass through the shank beside the pins (36G).
대표청구항▼
1. A turbine airfoil and platform assembly comprising: a turbine airfoil extending from a shank;a platform bracketing a first portion of the shank;a first pair of opposed teeth extending laterally from the platform; anda second pair of opposed teeth extending laterally from a second portion of the s
1. A turbine airfoil and platform assembly comprising: a turbine airfoil extending from a shank;a platform bracketing a first portion of the shank;a first pair of opposed teeth extending laterally from the platform; anda second pair of opposed teeth extending laterally from a second portion of the shank that extends beyond the platform;wherein the platform is formed of first and second platform portions, the first platform portion comprising integral pins, the shank comprising respective through-holes for the pins, and the first and second platform portions are connected to each other by the pins passing through the through-holes and a bond between the pins and the second platform portion;wherein the pins are sufficiently undersized in the through-holes that they do not support a centrifugal load of the airfoil. 2. The turbine airfoil and platform assembly of claim 1, wherein the turbine airfoil and shank are integrally formed, the platform is formed of a suction side portion and a pressure side portion, and the two platform portions are bonded together at matching end-wall surfaces of the two platform portions around the first portion of the shank. 3. The turbine airfoil and platform assembly of claim 1, wherein the turbine airfoil and shank are formed integrally of a first material and the platform is formed of a different material than the first material. 4. The turbine airfoil and platform assembly of claim 1, wherein the teeth of the shank and the teeth of the platform slide axially into respective slots in a turbine rotor disk. 5. The turbine airfoil and platform assembly of claim 1, wherein the shank and the platform are not bonded together, and they comprise a geometry that allows them to slide relative to each other at least to an extent of differential thermal expansion during operational temperature changes. 6. The turbine airfoil and platform assembly of claim 1, wherein the airfoil comprises a cooling chamber, and the shank comprises coolant passages that pass beside the one of the pins and communicate between the cooling chamber and a radially inner end of the shank, wherein said one pin is fully sleeved in a material of the shank, and said one pin interconnects the first and second portions of platform without a hole for said one pin in the platform that extends to an outer surface of the platform. 7. The turbine airfoil and platform assembly of claim 1, wherein the first platform portion comprises three pins that pass through respective pin holes in the shank and interconnect the first and second portions of the platform on opposed sides of the shank, wherein the shank comprises coolant passages that communicate between a cooling chamber in the airfoil and a radially inner end of the shank, wherein the coolant passages pass on each side of a central one of the pins that is fully sleeved in a material of the shank. 8. A turbine airfoil and platform assembly comprising: a turbine airfoil extending from a shank;a platform bracketing a first portion of the shank;a first pair of opposed teeth extending laterally from the platform;a second pair of opposed teeth extending laterally from a second portion of the shank that extends beyond the platform; anda third pair of opposed teeth extending laterally from the first portion of the shank within the platform, the third pair of opposed teeth engaging corresponding sockets in the platform, wherein centrifugal loads are shared between the shank and the platform. 9. A turbine airfoil and platform assembly comprising: a turbine airfoil extending from a shank;a platform comprising opposed pressure and suction side portions bracketing a first portion of the shank;a first pair of opposed teeth extending laterally respectively from the opposed pressure and suction side portions of the platform;a second pair of opposed teeth extending laterally from a second portion of the shank extending outside the platform;a pin passing through a pin hole in the shank and interconnecting the pressure and suction side portions of the platform;wherein the pin engages the platform without a hole therefore extending to an outer surface of the platform;a cooling chamber in the turbine airfoil;cooling passages communicating between the cooling chamber and a radially inner end of the shank;the cooling passages branching around a wall of the pin hole. 10. The turbine airfoil and platform assembly of claim 8, wherein the platform is bi-cast onto the first portion of the shank. 11. The turbine airfoil and platform assembly of claim 8, wherein the second pair of opposed teeth on the shank and the teeth of the platform slide axially into respective slots in a turbine rotor disk. 12. The turbine airfoil and platform assembly of claim 8, wherein the shank and the platform are not bonded together, and they comprise a geometry that allows them to slide relative to each other at least to an extent of differential thermal expansion during operational temperature changes. 13. The turbine airfoil and platform assembly of claim 9, wherein the two platform portions are bonded together at matching end-wall surfaces of the two platform portions around the first portion of the shank. 14. The turbine airfoil and platform assembly of claim 9, wherein the turbine airfoil and shank are formed integrally of a first material and the platform is formed of a different material than the first material. 15. The turbine airfoil and platform assembly of claim 9, wherein the platform is bi-cast onto the first portion of the shank. 16. The turbine airfoil and platform assembly of claim 9, wherein the teeth of the shank and the teeth of the platform slide axially into respective slots in a turbine rotor disk. 17. The turbine airfoil and platform assembly of claim 9, wherein the shank and the platform are not bonded together, and they comprise a geometry that allows them to slide relative to each other at least to an extent of differential thermal expansion during operational temperature changes. 18. The turbine airfoil and platform assembly of claim 9, wherein the pin is sufficiently undersized in the pin hole that it does not support a centrifugal load of the airfoil.
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