Locking arrangement for radial entry turbine blades
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B63H-001/20
B63H-001/00
출원번호
US-0088639
(2005-03-24)
등록번호
US-7261518
(2007-08-28)
발명자
/ 주소
Golinkin,Samuel
Lipski,Michael J.
Loudon,John S.
DiOrio,Gennaro J.
Ewer,Timothy
출원인 / 주소
Siemens Demag Delaval Turbomachinery, Inc.
인용정보
피인용 횟수 :
11인용 특허 :
33
초록▼
A locking arrangement for a row of radial entry blades (62) of a turbo-machine. A closing blade (66) includes a root portion (74) having an axial attachment shape (78) for engagement with an axially oriented slot having an axial attachment shape (76) formed at the entering slot location (34) of the
A locking arrangement for a row of radial entry blades (62) of a turbo-machine. A closing blade (66) includes a root portion (74) having an axial attachment shape (78) for engagement with an axially oriented slot having an axial attachment shape (76) formed at the entering slot location (34) of the radial entry rotor disk (56). For applications utilizing blades with curved platform faces (112), a preceding blade (108) and a following blade (110) in the row are designed with one curved face for abutting adjacent radial entry blades and one flat face (120) for abutting the flat closing blade faces (116). The closing blade (84) may be designed with a root portion (88) having two legs (90,92) that are urged apart by a key (86) into tight contact with the adjacent blades.
대표청구항▼
The invention claimed is: 1. A rotating element for a turbo-machine comprising: a rotor disk; a first radial attachment shape formed along a circumference of the disk; a first axial attachment shape formed in the circumference of the rotor disk at an entering slot location; a plurality of radial en
The invention claimed is: 1. A rotating element for a turbo-machine comprising: a rotor disk; a first radial attachment shape formed along a circumference of the disk; a first axial attachment shape formed in the circumference of the rotor disk at an entering slot location; a plurality of radial entry blades each comprising a root portion comprising a second radial attachment shape complementary to and engaged with the first radial attachment shape, the plurality of radial entry blades disposed along the circumference of the rotor disk at locations other than the entering slot location; and a closing blade disposed at the entering slot location and comprising a root portion comprising a second axial attachment shape complementary to and engaged with the first axial attachment shape. 2. The rotating element of claim 1, further comprising a contact pin disposed between the closing blade and an adjoining one of the plurality of radial entry blades. 3. The rotating element of claim 2, wherein the contact pin comprises a material exhibiting a coefficient of thermal expansion that is greater than respective coefficients of thermal expansion of materials of the closing blade and adjoining radial entry blade. 4. The rotating element of claim 1, further comprising: a root portion of the closing blade comprising a first leg and a second leg; a key disposed between the first and second legs for urging the root portion into contact with the disk. 5. The rotating element of claim 4, wherein the key comprises a double dog bone shape. 6. The rotating element of claim 4, wherein the key comprises a material different from a material of the root portion. 7. The rotating element of claim 4, wherein the material of the key exhibits higher yield strength than the material of the root portion. 8. The rotating element of claim 4, wherein the material of the key exhibits a coefficient of thermal expansion higher than the material of the root portion. 9. The rotating element of claim 4, wherein the material of the connecting member portion exhibits a coefficient of thermal expansion greater than the material of the radial entry blade portion. 10. The rotating element of claim 1, wherein the closing blade further comprises: a radial entry blade portion substantially identical to respective ones of the plurality of radial entry blades and comprising a root portion comprising the second radial attachment shape; and a connecting member portion comprising a radial attachment portion comprising the first radial attachment shape for engagement with the root portion of the radial entry blade portion, and an axial attachment portion comprising the second axial attachment shape engaged with the first axial attachment shape formed in the disk at the entering slot location. 11. The rotating element of claim 10, further comprising a contact pin disposed between the radial entry blade portion of the closing blade and an adjoining one of the plurality of radial entry blades. 12. The rotating element of claim 10, wherein the connecting member portion comprises a material different from a material of the radial entry blade portion. 13. The rotating element of claim 12, wherein the material of the connecting member portion exhibits a higher yield strength than the material of the radial entry blade portion. 14. The rotating element of claim 1, further comprising: each of the plurality of radial entry blades comprising a complementary pair of opposed curved faces; the closing blade comprising a pair of opposed flat faces; a preceding blade disposed adjacent a first side of the closing blade, the preceding blade comprising a root portion comprising the second radial attachment shape engaged with the first radial attachment shape, a curved face abutting an adjacent one of the plurality of radial entry blades, and a flat face abutting a first of the opposed flat faces of the closing blade; and a following blade disposed adjacent a second side of the closing blade opposed the preceding blade, the following blade comprising a root portion comprising the second radial attachment shape engaged with the first radial attachment shape, a curved face abutting an adjacent one of the plurality of radial entry blades, and a flat face abutting a second of the opposed flat faces of the closing blade. 15. The rotating element of claim 14, further comprising a contact pin disposed between the closing blade and one of the preceding blade and the following blade. 16. The rotating element of claim 1, further comprising: the first and second radial attachment shapes each comprising one of a fir tree shape, a tee shank shape and a dog bone shape; and the first and second axial attachment shapes each comprising one of a fir tree shape, a tee shank shape and a dog bone shape. 17. The rotating element of claim 1, wherein the closing blade root portion comprises an insertion axis parallel to an axis of a rotor associated with the rotor disk. 18. The rotating element of claim 1, wherein the closing blade root portion comprises an insertion axis transverse to an axis of a rotor associated with the rotor disk. 19. A turbo-machine comprising the rotating element of claim 1. 20. The rotating element of claim 1, further comprising: an axially arranged slot formed in the disk at the entering slot location; and a key comprising a radially inner portion configured for axial insertion into the axially arranged slot and a radially outer portion configured for engaging a root portion of the closing blade. 21. The locking arrangement of claim 20, wherein the key comprises a material different from a material of the rotor disk. 22. The locking arrangement of claim 20, wherein the key comprises a material different from a material of the root portion of the closing blade. 23. A turbo-machine comprising the rotating element of claim 20. 24. A rotating element for a turbo-machine comprising: a generally disk shaped member comprising a circumference; a radial attachment shape formed along the circumference for locating a plurality of radial entry blades in a row; and an axial slot formed at a radial blade entry location of the circumference and comprising an axial attachment shape for receiving a closing blade and for securing the closing blade during operation of the turbo-machine; wherein the axial attachment shape comprises a dog bone shape. 25. The rotating element of claim 24, wherein the radial attachment shape comprises one of an internal fir tree, an external fir tree and a T-shank shapes. 26. The rotating element of claim 24, wherein the axial slot is disposed along an insertion axis parallel to a rotating axis of the rotating element. 27. The rotating element of claim 24, wherein the axial slot is disposed along an insertion axis transverse to a rotating axis of the rotating element. 28. A turbo-machine comprising the rotating element of claim 24. 29. A closing blade group for a row of radial entry turbine blades having curved root/platform faces, the group comprising: a closing blade comprising an airfoil portion, a platform portion comprising a pair of opposed flat faces, and a root portion comprising an axial attachment shape complementary to an axial attachment shape formed in a rotor at an entering slot location; a preceding blade comprising an airfoil portion, a platform portion comprising a curved face for abutting an adjacent radial entry blade and an opposed flat face for abutting a first of the flat faces of the closing blade, and a root portion comprising a first radial attachment shape complementary to a second radial attachment shape formed about a circumference of the rotor; and a following blade comprising an airfoil portion, a platform portion comprising a flat face for abutting a second of the flat faces of the closing blade and an opposed curved face for abutting an adjacent radial entry blade, and a root portion comprising the first radial attachment shape. 30. The group of claim 29, wherein the pair of opposed flat faces of the closing blade are disposed parallel to a rotational axis of the rotor. 31. The group of claim 29, wherein the pair of opposed flat faces of the closing blade are disposed transverse to a rotational axis of the rotor and parallel to an insertion axis of the axial attachment shape of the closing blade. 32. The group of claim 29, wherein the radial attachment shape comprises one of an internal fir tree, an external fir tree and a T-shank shapes. 33. The group of claim 29, wherein the axial attachment shape comprises a dog bone shape. 34. A turbo-machine comprising the closing blade group of claim 29. 35. A method of securing a row of radial entry blades onto a turbine rotor disk, the method comprising: forming a first radial attachment shape along a circumference of the rotor disk; forming an entering slot location on the circumference of the rotor disk; forming a first axial attachment shape at the entering slot location; installing onto the circumference of the rotor disk via the entering slot location a plurality of radial entry blades comprising a second radial attachment shape complementary to and engaged with the first radial attachment shape; and installing at the entering slot location an axial entry closing blade comprising a second axial attachment shape complementary to and engaged with the first axial attachment shape. 36. The method of claim 35, further comprising installing a contact pin between the closing blade and an adjacent radial entry blade. 37. The method of claim 35, further comprising forming the closing blade to comprise a root portion comprising two legs and an axial key portion disposed between the two legs and extending to form the second axial attachment shape. 38. The method of claim 35, further comprising forming the axial key portion of a material different from a material of the platform portion. 39. The method of claim 35, further comprising forming the closing blade to comprise a radial entry blade portion substantially identical to ones of the plurality of radial entry blades and a connecting member portion comprising a radial attachment portion comprising the first radial attachment shape for engagement with the radial entry blade portion and an axial attachment portion comprising the second axial attachment shape. 40. The method of claim 35, further comprising forming the first and second axial attachment shapes to have an insertion axis parallel to a rotational axis of the disk. 41. The method of claim 35, further comprising forming the first and second axial attachment shapes to have an insertion axis transverse to a rotational axis of the disk. 42. A method of modifying a radial entry turbo-machine rotor disk as applied to a rotor disk supporting blades having curved platform faces, the method comprising: removing material containing a flaw from a periphery portion of a radial entry rotor disk to form an axial attachment shape; installing an axial entry blade onto the radial entry rotor disk in engagement with the axial attachment shape; providing the axial entry blade to have two opposed flat platform faces; installing a radial entry protecting blade and a radial entry following blade adjacent the axial entry blade, each of the preceding blade and the following blade comprising a flat platform face for abutting a respective one of the two axial entry blade flat platform faces, and each of the preceding blade and the following blade comprising an opposed curved platform face for abutting an adjacent radial entry blade. 43. The method of claim 42, further comprising installing a contact pin between the axial entry blade and at least one adjacent radial entry blade installed on the rotor disk. 44. The method of claim 42, further comprising forming the flat platform faces of the preceding blade, the following blade and the closing blade to be parallel to an axis of rotation of the disk. 45. The method of claim 42, further comprising forming the flat platform faces of the preceding blade, the following blade and the closing blade to be transverse to an axis of rotation of the disk.
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이 특허에 인용된 특허 (33)
Pisz Frank A. (Titusville FL) McLaurin Leroy D. (Winter Springs FL) Gergely George A. (Stuart FL) Donlan John P. (Oviedo FL), Apparatus for locking side entry blades into a rotor.
Partington Doretta H. (Winter Springs FL) Partington Albert J. (Winter Springs FL), Method for assembling side entry control stage blades in a steam turbine.
Hansen Kurt L. (Schenectady NY) VanDenburgh Ronald J. (Ballston Lake NY), Method for assembly of tangential entry dovetailed bucket assemblies on a turbomachine bucket wheel.
Yazdzik ; Jr. Henry (Rocky Hill CT) Reed Gordon M. (Plantsville CT) Estes Vernon E. (Carlisle PA) Walker Herbert L. (Glastonbury CT), Method for making gas turbine engine blade attachment slots.
Wilson Ian L. W. (Murrysville PA) Clark ; Jr. William G. (Murrysville PA) Radford Kenneth C. (North Huntingdon PA), Process for securing a turbine blade.
Moroso, Joseph Leonard, Radial retainer for single lobe turbine blade attachment and method for radially retaining a turbine blade in a turbine blade slot.
Juenger Jerome A. (Cincinnati OH) Peterson Stephen C. (West Chester OH) Herzner Frederick C. (Fairfield OH), Stress-relieved rotor blade attachment slot.
Przytulski James C. (Fairfield OH) Horvath Richard L. (Hamilton OH) Stoughton Philip H. (Cincinnati OH) Glynn Christopher C. (Hamilton OH) Wesling Richard A. (Cincinnati OH) Corsmeier Robert J. (Cinc, Turbine blade inner end attachment structure.
Caruso David A. (Schenectady NY) Deallenbach Robert E. (Schenectady NY) Gordon William D. (Scotia NY) Jones Raymond J. (Duanesburg NY) Morson Alexander (Clifton Park NY), Turbine bucket and wheel assembly with integral bucket shroud.
Willett, Jr., Fred Thomas; Duclos, Laurence Scott; Mack, Michael Dennis; McMurray, Timothy Scott; Swintek, Roy Paul, Turbine rotor insert and related method of installation.
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