US3721506A - Split-nut blade locking assembly - Google Patents

Split-nut blade locking assembly Download PDF

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Publication number
US3721506A
US3721506A US00146732A US3721506DA US3721506A US 3721506 A US3721506 A US 3721506A US 00146732 A US00146732 A US 00146732A US 3721506D A US3721506D A US 3721506DA US 3721506 A US3721506 A US 3721506A
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United States
Prior art keywords
split
nut
groove
set screw
blades
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Expired - Lifetime
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US00146732A
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English (en)
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B Anderson
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General Electric Co
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General Electric Co
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • ABSTRACT l l A split-nut blade locking assembly, for maintaining the 0 Search l l 5, 2 l 6, circumferential integrity of blades peripherally disposed within a groove around a rotor element in- References Cited cludes a split-nut within which a set screw may be UNITED STATES PATENTS threadably engaged for s areading apart the halves of the split-nut and maintaining the halves in engagement 1,687,891 10/1928 Ray 416/216 with the side walls of the groove. 2,315,631 4/1943 Lloyd et alm.
  • this invention relates to a split-nut blade locking assembly and more particularly to a split-nut blade locking assembly for securing a plurality of circumferentially spaced blades disposed about the periphery ofa rotor disc.
  • each blade so disposed includes a vane section extending outward from the periphery of the rotor disc and a root portion extending in a substantially inward radial direction from the periphery of the rotor disc. It is also well known in the art to radially and axially retain the blades in the rotor by means of a dovetail groove around the outer periphery thereof.
  • the blade root portions are thickened at the inner radial end to provide outwardly extending shoulders which abut the inwardly directed faces of the dovetail groove.
  • Assembly of the blade roots into the dovetail groove is ordinarily accomplished by inserting a blade root through a narrow, square-cornered entrance slot, cut into the dovetail groove at one or more discreet points along the circumference of the spool and then sliding the blades in the dovetail groove into their respective positions.
  • Means must be provided for locking the blades in circumferential position along the periphery of the rotor disc.
  • the locking means must be capable of withstanding the circumferential component of the aerodynamic load developed during compressor operation.
  • the locking device must be capable of permitting assembly and disassembly of the blade members to the spool with relative ease.
  • Past means have often taken the form of set screw arrangements or spring load devices which have reliability limitations, or are difficult to contend with during assembly and disassembly of the rotor. These devices are of very small physical size and are, therefore, often limited in strength.
  • Other shortcomings of prior art devices relate to the necessity that the entire circumferential row of blades be rotated as a unit, one-half a blade pitch about the periphery of the rotor disc at assembly and disassembly. This often results in damaged blades due to the tendency of blades to seize after prolonged service. Also, conventional locking means are often visually concealed after all blades are inserted thereby prohibiting subsequent visual inspection.
  • the split-nut blade locking assembly of this invention includes a wrenching set screw and a split-nut positioned within a dovetail groove.
  • the wrenching set screw has an external thread around the body thereof.
  • the split-nut includes a split-collar wherein the inside surface of the split-collar includes a screw thread for threadably engaging the set screw.
  • the two arcuate segments of the split-collar further include flange members having sides which extend outwardly into shoulders adapted for engagement with the inwardly directed faces of a dovetail groove. Threadably engaging the set screw within the split-nut acts to spread apart the halves of the split-nut and maintain the shoulders in engagement with the faces of the dovetail groove. 4
  • FIG. 1 is a perspective view showing the locking assembly of this invention as assembled within a rotor disc.
  • FIG. 2 is an exploded perspective view showing the locking assembly of FIG. 1 in combination with a rotor disc.
  • FIG. 3 is a perspective view showing a rotor blade positioned within an entrance slot in the periphery of the rotor.
  • FIG. 4 is a cross-sectional view of FIG. 1 taken along the line 4-4.
  • FIG. 5 is an exploded perspective view showing an alternate embodiment for the locking assembly of FIGS. 1 and 2 in combination with a rotor disc.
  • FIG. 1 shows a portion of a rotor assembly 10 of the type commonly included in an axial flow compressor which may form an integral part of a gas turbine engine.
  • the rotor assembly 10 is shown as including a rotor disc 11 having axially spaced apart, opposed faces 12 and 14, both of which are substantially normal to the axis of rotor rotation.
  • the rotor disc 11 includes a plurality of circumferentially spaced apart blades 22 and 24 disposed about its periphery.
  • the blades 24 and end locking blades specially adapted to accommodate the split nut blade locking assembly of this invention shown generally at 37 and which will hereinafter be described in full detail.
  • Each of the blades 22, 24 includes an airfoil vane section 26 through which gas flow may be directed for compression in a manner well known to the art.
  • the blades 22, 24 also include platforms 28, 30
  • dovetail root portions 32 extend in substantially inward radial directions.
  • the platforms generally overhang the root portions.
  • the blades 22, 24 are radially and axially retained by means of a circumferential dovetail groove 16 extending around the outer periphery of the rotor disc 11.
  • the dovetail groove 16 includes a pair of side walls 18 which are undercut to provide inwardly directed abutment faces 20.
  • Each dovetail root 32 is thickened at the inner radial end to provide outwardly extending shoulders 34 which abut the inwardly directed faces of the dovetail groove, thereby radially retaining the blades under centrifugal loading.
  • the circumferential dovetail groove 16 includes a circular entrance slot 36 therein, to accommodate insertion of the individual blade root portions 32 into the dovetail groove 16.
  • Each blade root portion 32 is individually inserted through the circular entrance slot 36 for engagement with the opposing surfaces of the dovetail groove 16.
  • each blade 22 is circumferentially slid around the dovetail groove 16 into platform abutting relation with an adjacent blade until all the inserted blades circumferentially fill the dovetail groove.
  • the last two blades to be inserted are the end locking blades 24.
  • the circular entrance slot 36 is of sufficiently large radius to accommodate insertion of the substantially rectangular cross-sectional root portion 32 of the end locking blade 24.
  • the root portions ofthe conventional blades 22 are identical to the root portions of the end locking blades 24, and are inserted into the entrance slot for engagement with the dovetail groove in like manner. All of the root portions 32 include opposing transverse faces 35, 35' extending across the dovetail groove.
  • the opposing transverse faces 35, 35 generally lie in the plane of intersection of a rotor radius with the central axis of rotation, and are normal to the side walls 18 of the circumferential dovetail groove 16.
  • the opposing transverse faces 35, 35 are not inherently limited to any particular plane and may be skewed in relation to the side walls 18 of the dovetail groove 16.
  • the locking blade platforms are indented along the edges 56, 56' so as to align the edges of the blade platforms with the respective transverse faces 35, of the root portions. Even though the locking blade platforms 30 are indented along the edges 56, 56' an additional space equal to as much as half a blade pitch may still remain between the end locking blade vanes after insertion of the split-nut locking assembly. This spacing, however, has been found not to adversely affect engine performance.
  • the split-nut locking assembly is also shown in FIG. 2 at 37 as including a split-nut 38 and an internal wrenching set screw 46.
  • the use of a split-nut together with a circular entrance slot makes possible the inclusion of a larger set screw than heretofore possible with the smaller conventional square cornered locking slots.
  • the split-nut 38 includes a split collar 39 having two arcuate segments 40, 40'. Outside surfaces 41, 41' of arcuate segments 40, 40' are proportioned for abutting engagement with the inside surfaces of the circular entrance slot 36.
  • Arcuate segments 40, 40' of the splitcollar 39 respectively include flange members 43, 43.
  • the flange members 43, 43' respectively have outwardly extending shoulders 44, 44' for engagement with the inwardly directed abutment faces 20 of the sidewalls 18 of the dovetail grooves 16.
  • the ends of the flange members 43, 43' cooperate together to form split-transverse abutment faces 54, 54'.
  • the split-collar 39 includes an internal screw thread which is threadably engaged to the external screw thread of the wrenching set screw 46.
  • the wrenching set screw 46 also includes a hexagonal insert 52 in the top surface thereof, adapted for receiving an Allen wrench or the like.
  • the split-nut 38 is inserted into the area of the circular entrance slot 36 and dovetail groove 16 in a manner so that the outer surfaces 41, 41' of the arcuate segments of the split-collar 39 abut the interior surfaces of the circular entrance slot and each outwardly extending shoulder 44, 44' engages a corresponding inwardly directed abutment face 20 of the dovetail groove 16.
  • the split-transverse abutment faces 35, 35' engage the respective transverse faces 35, 35' of the root portions 32 of the locking blades 24.
  • the split halves of the nut 38 are spread apart and maintained in abutting and engaging relation with the dovetail groove 16 by insertion of the wrenching set screw 46 which threadably engages the split-nut 38.
  • the wrenching set screw 46 may be safety locked into position by peening over the top thread on the split-nut 38. Therefore, the split-nut 38 is preferably made from a softer and more ductile material than the wrenching set screw 46 to facilitate peening and to make it possible to disassemble by threading the set screw out, so as to reform the peened thread.
  • circumferential sliding of the split-nut blade retention assembly 37 around the peripheral dovetail groove of the rotor disc 11 is inhibited by the abutting relation of the outside surfaces 41, 41' of the split-collar with the inside surface of the circular entrance slot 36.
  • Circumferential sliding of the blades 22, 24 around the peripheral dovetail groove of the rotor disc 11 is positively inhibited by the abutting relation of the splittransverse abutment faces 54, 54' with the respective transverse faces 35, 35' of the root portions 32 of the locking blades 24.
  • Radial withdrawal of the split-nut blade retention assembly is also prohibited by engagement of the outwardly extending shoulders 44,44 with the inwardly directed abutment faces of the dovetail groove 16.
  • the split-nut blade retention assembly may be withdrawn by inserting an Allen wrench or the like into the hexagonal insert 52 in the top surface of the set screw 46 and threadably disengaging the set screw from the split-nut. After the set screw is withdrawn, the splitnut may be removed, whereupon each blade may be circumferentially slid into the area of the circular entrance slot 36 and withdrawn in a generally radial direction.
  • an Allen wrench or the like into the hexagonal insert 52 in the top surface of the set screw 46 and threadably disengaging the set screw from the split-nut.
  • the splitnut may be removed, whereupon each blade may be circumferentially slid into the area of the circular entrance slot 36 and withdrawn in a generally radial direction.
  • the wrenching set screw 46 be formed with double lead threads around the body thereof.
  • the double lead threads are shown in FIG. 2 as including a primary lead thread 48 and a secondary lead thread 50, wherein both ends of the primary and secondary threads are 180 apart from each other on the circumference of the screw.
  • the split-nut 38 also would include internal double lead threads for threadably receiving the set screw 46.
  • the double lead threads are preferred because they permit the halves of the split-nut 39 to be interchanged thereby eliminating the need to match the halves of each split-nut.
  • insert 52 on the top of the set screw 46 has been described as hexagonal in shape, it need not be so limited and may include any shape to which a tool may be keyed so as to provide increased torque so as to either tighten the set screw or remove the set screw once it has been tightened.
  • split-nut retention assembly is shown generally as including a split-nut 60 which consists, of a split-collar 61 having two arcuate segments 62, 62'. Again the outside surfaces of the arcuate segments are proportioned for abutting engagement with the inside surfaces of the circular entrance slot 36.
  • Arcuate segments 62, 62' of the split-collar 61 include respectively flange members 63, 63.
  • the flange members 63, 63' respectively include shoulders 64, 64 extending outwardly in opposing directions for engagement with the inwardly directed abutment faces 20 of the sidewalls 18 of the dovetail slot 36.
  • the halves of the split nut are then spread apart so that the outwardly extending shoulders 64, 64. engage the inwardly directed abutment faces 20 of the dovetail groove and the transverse faces 66, 66' abut respectively opposing transverse faces 35, 35' of the blade roots.
  • the split halves of the nut are maintained in spread apart relation by insertion of the wrenching set screw 46 which threadably engages the split-nut 60. Withdrawal of the locking assembly may be accomplished by reversing the previously described process.
  • a split-nut locking assembly for attachment to a groove comprising:
  • a wrenching set screw having an external thread around the body thereof
  • split-nut including a split-collar having two arcuate segments, the inside surfaces of which are threaded for threadably engaging the set screw, and wherein the arcuate segments of the split-collar integrally connect to flange members having sides which extend outwardly into shoulders adapted for engagement with the sidewalls of the groove when the set screw is threadably engaged within the split-nut so as to spread apart the halves of the split-nut.
  • a split-nut locking assembly for locking a plurality of circumferentially spaced blades disposed about the outer periphery of a grooved rotor disc comprising:
  • a wrenching set screw having an external thread around the body thereof
  • split-nut including a split-collar having two arcuate segments, the inside surfaces of which are threaded for threadably engaging the set screw, and wherein the arcuate segments of the split-cob lar integrally connect to flange members having sides which extend outwardly into shoulders adapted for engagement with the sidewalls of the groove when the set screw is threadably engaged within the split-nut so as to spread apart the halves of the split-nut.
  • the side walls of the groove are undercut to provide inwardly directed abutment faces for engaging the outwardly extending shoulders of the split-nut and including at least one circular entrance slot through the inwardly directed abutment faces of the groove to accommodate insertion of the flange members ofthe split-nut within the groove, and
  • each blade has a vane section extending outward from the periphery of the rotor disc and a root portion extending in a substantially inward radial direction from the periphery of the rotor disc, with each root thickened at the inner radial end to provide outwardly extending shoulders which abut the inwardly directed faces of the groove so as to radially and axially retain the blades with circumferential retention of the blades along the peripheral groove maintained by the split-nut the outwardly extending shoulders of which also engage the inwardly directed faces of the groove upon threadable engagement of the set screw within the split-nut.
  • each blade includes an overhanging platform disposed between the vane and root portion such that the blades may be circumferentially arranged around the peripheral groove in platform abutting relation and wherein the platforms of the two blades adjacent the split-nut are indented to accommodate insertion of the split-nut while maintaining a minimum arc distance between the blades adjacent to the split-nut.
  • each blade root portion includes a pair of opposing transverse faces extending across the dovetail groove
  • each flange member of an arcuate segment of the split-collar includes an outwardly extending shoulder for engagement with a face of the groove and the respective ends of both flanges cooperate together to form split transverse faces such that circumferential sliding of the splitnut and set screw around the peripheral groove of the rotor disc is inhibited by abutment between the outside surface of the split collar with the inside surface of the circular entrance slot, circumferential sliding of the blades around a the peripheral groove of the rotor disc is inhibited by abutment between the split transverse faces of the split-nut and the respective transverse faces of the blade root portions and outward radial withdrawal of the split-nut is prohibited by engagement of the outwardly extending shoulders with the inwardly directed abutment faces of the peripheral groove.
  • each blade root portion includes a pair of opposing transverse faces extending across the dovetail groove
  • each flange member of an arcuate segment of the split-collar includes a pair of oppositely extending shoulders for engagement with the opposing faces of the groove and the end of each flange terminates in a transverse face
  • circumferential sliding of the split-nut and set screw around the peripheral groove of the rotor disc is inhibited by abutment between the outside surface of the split-collar with the inside surface of the circular entrance slot
  • circumferential sliding of the blades around the peripheral groove of the rotor disc is inhibited by abutment between the transverse faces of the split-nut and the respective transverse faces of the blade root portions and outward radial withdrawal of the split-nut is prohibited by engagement of the outwardly extending shoulders with the inwardly directed abutment faces of the peripheral groove.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00146732A 1971-05-25 1971-05-25 Split-nut blade locking assembly Expired - Lifetime US3721506A (en)

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US14673271A 1971-05-25 1971-05-25

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US (1) US3721506A (enrdf_load_stackoverflow)
BE (1) BE779225A (enrdf_load_stackoverflow)
CA (1) CA952820A (enrdf_load_stackoverflow)
CH (1) CH565319A5 (enrdf_load_stackoverflow)
DE (1) DE2207561A1 (enrdf_load_stackoverflow)
FR (1) FR2138612B1 (enrdf_load_stackoverflow)
GB (1) GB1386821A (enrdf_load_stackoverflow)
NL (1) NL7201197A (enrdf_load_stackoverflow)
SE (1) SE379402B (enrdf_load_stackoverflow)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902824A (en) * 1974-07-29 1975-09-02 Gen Motors Corp Blade lock
US4255086A (en) * 1979-06-27 1981-03-10 Pratt & Whitney Aircraft Of Canada Limited Locking device for blade mounting
US4859149A (en) * 1989-03-10 1989-08-22 General Motors Corporation Blade locking system
RU2189023C2 (ru) * 2001-02-02 2002-09-10 ООО "Самаратрансгаз" Замковое устройство
US6499959B1 (en) * 2000-08-15 2002-12-31 General Electric Company Steam turbine high strength tangential entry closure bucket and retrofitting methods therefor
US6638006B2 (en) * 2001-02-03 2003-10-28 Rolls-Royce Plc Turbine blade locking device
US6647602B2 (en) * 2000-12-16 2003-11-18 Alstom (Switzerland) Ltd Fixation device for blading of a turbo-machine
US20060222502A1 (en) * 2005-03-29 2006-10-05 Siemens Westinghouse Power Corporation Locking spacer assembly for a turbine engine
EP1801355A1 (fr) * 2005-12-23 2007-06-27 Techspace aero Dispositif pour bloquer les aubes d'un disque de turbomachine
EP1803900A1 (de) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Schlussbaugruppe zum Schliessen des verbleibenden Zwischenraums zwischen der ersten und der letzten in einer Umfangsnut einer Strömungsmaschine eingesetzten Schaufel eines Schaufelkranzes und entsprechende Strömungsmaschine
US20070297908A1 (en) * 2006-06-23 2007-12-27 Siemens Power Generation, Inc. Turbine rotor blade groove entry slot lock structure
US20090220345A1 (en) * 2006-01-02 2009-09-03 Siemens Aktiengesellschaft Closing Assembly for a Blade Ring of Turbomachinery
CN102220885A (zh) * 2010-04-16 2011-10-19 通用电气公司 用于周向附接装置的锁定组件
US20120114490A1 (en) * 2010-11-10 2012-05-10 General Electric Company Turbine assembly and method for securing a closure bucket
CN103174463A (zh) * 2011-12-21 2013-06-26 通用电气公司 涡轮转子插入件和相关的安装方法
US20130170996A1 (en) * 2012-01-03 2013-07-04 General Electric Company Rotor blade mounting
JP2013221517A (ja) * 2012-04-16 2013-10-28 General Electric Co <Ge> ターボ機械動翼取付けシステム
US20140286782A1 (en) * 2012-08-07 2014-09-25 Solar Turbines Incorporated Turbine blade staking pin
US20150101347A1 (en) * 2013-10-16 2015-04-16 General Electric Company Locking spacer assembly
US20170191371A1 (en) * 2014-04-15 2017-07-06 Siemens Aktiengesellschaft Wheel disc with at least one sealing plate
US9903408B2 (en) * 2016-07-28 2018-02-27 Tsun-Chi Liao Fast-dismounted cymbal-locking nut
US10024164B2 (en) * 2016-09-27 2018-07-17 General Electric Company Fixture for restraining a turbine wheel
US10100677B2 (en) * 2016-09-27 2018-10-16 General Electric Company Fixture for restraining a turbine wheel
CN111954751A (zh) * 2018-04-18 2020-11-17 西门子公司 锁定间隔器组件、相对应的叶片组件、用于安装锁定间隔器的方法
US10858941B2 (en) * 2018-05-23 2020-12-08 Safran Aircraft Engines Shutter for turbine machine having an absent rectifier blade
CN115217529A (zh) * 2021-04-20 2022-10-21 中国航发商用航空发动机有限责任公司 转子叶片的锁紧装置

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DE19826897A1 (de) * 1998-06-17 1999-12-23 Abb Patent Gmbh Schloß für Laufschaufeln eines Turbinenläufers
DE102016219837A1 (de) * 2016-10-12 2018-04-12 Siemens Aktiengesellschaft Rotor und Verfahren zur Montage von Laufschaufeln unter Verwendung von schmäleren Schaufelplattformen

Cited By (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902824A (en) * 1974-07-29 1975-09-02 Gen Motors Corp Blade lock
US4255086A (en) * 1979-06-27 1981-03-10 Pratt & Whitney Aircraft Of Canada Limited Locking device for blade mounting
US4859149A (en) * 1989-03-10 1989-08-22 General Motors Corporation Blade locking system
US6499959B1 (en) * 2000-08-15 2002-12-31 General Electric Company Steam turbine high strength tangential entry closure bucket and retrofitting methods therefor
US6647602B2 (en) * 2000-12-16 2003-11-18 Alstom (Switzerland) Ltd Fixation device for blading of a turbo-machine
RU2189023C2 (ru) * 2001-02-02 2002-09-10 ООО "Самаратрансгаз" Замковое устройство
US6638006B2 (en) * 2001-02-03 2003-10-28 Rolls-Royce Plc Turbine blade locking device
US7435055B2 (en) 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
US20060222502A1 (en) * 2005-03-29 2006-10-05 Siemens Westinghouse Power Corporation Locking spacer assembly for a turbine engine
EP1801355A1 (fr) * 2005-12-23 2007-06-27 Techspace aero Dispositif pour bloquer les aubes d'un disque de turbomachine
US8157530B2 (en) 2006-01-02 2012-04-17 Siemens Aktiengesellschaft Locking sub-assembly for closing the remaining gap between the first and the last of a blade ring which are inserted in a circumferential groove of a turbomachine, and corresponding turbomachine
CN101351620B (zh) * 2006-01-02 2012-06-13 西门子公司 用于对在叶片环的装在流体机械的环形槽中的第一个和最后一个叶片之间留下的中间空隙进行封闭的闭锁组件以及相应的流体机械
WO2007077183A1 (de) * 2006-01-02 2007-07-12 Siemens Aktiengesellschaft Schlüssbaugruppe zum schliessen des verbleibenden zwischenraums zwischen der ersten und der letzten in einer umfangsnut einer strömungsmaschine eingesetzten schaufel eines schaufelkranzes und entsprechende strömungsmaschine
US20090016889A1 (en) * 2006-01-02 2009-01-15 Joachim Krutzfeldt Locking Sub-Assembly for Closing The Remaining Gap Between The First and The Last blade of a Blade Ring Which Are Inserted in a Circumferential Groove of a Turbomachine, and Corresponding Turbomachine
US20090220345A1 (en) * 2006-01-02 2009-09-03 Siemens Aktiengesellschaft Closing Assembly for a Blade Ring of Turbomachinery
RU2392446C2 (ru) * 2006-01-02 2010-06-20 Сименс Акциенгезелльшафт Запорный блок для лопаточного венца лопаточной машины
US8157531B2 (en) * 2006-01-02 2012-04-17 Siemens Aktiengesellschaft Closing assembly for a blade ring of turbomachinery
EP1803900A1 (de) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Schlussbaugruppe zum Schliessen des verbleibenden Zwischenraums zwischen der ersten und der letzten in einer Umfangsnut einer Strömungsmaschine eingesetzten Schaufel eines Schaufelkranzes und entsprechende Strömungsmaschine
US7901187B2 (en) 2006-06-23 2011-03-08 Siemens Energy, Inc. Turbine rotor blade groove entry slot lock structure
US20070297908A1 (en) * 2006-06-23 2007-12-27 Siemens Power Generation, Inc. Turbine rotor blade groove entry slot lock structure
CN102220885A (zh) * 2010-04-16 2011-10-19 通用电气公司 用于周向附接装置的锁定组件
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
US8714929B2 (en) * 2010-11-10 2014-05-06 General Electric Company Turbine assembly and method for securing a closure bucket
US20120114490A1 (en) * 2010-11-10 2012-05-10 General Electric Company Turbine assembly and method for securing a closure bucket
CN103174463B (zh) * 2011-12-21 2016-05-11 通用电气公司 涡轮转子插入件和相关的安装方法
US20130164138A1 (en) * 2011-12-21 2013-06-27 General Electric Company Turbine rotor insert and related method of installation
US8894372B2 (en) * 2011-12-21 2014-11-25 General Electric Company Turbine rotor insert and related method of installation
CN103174463A (zh) * 2011-12-21 2013-06-26 通用电气公司 涡轮转子插入件和相关的安装方法
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Also Published As

Publication number Publication date
SE379402B (enrdf_load_stackoverflow) 1975-10-06
BE779225A (fr) 1972-05-30
NL7201197A (enrdf_load_stackoverflow) 1972-11-28
FR2138612A1 (enrdf_load_stackoverflow) 1973-01-05
DE2207561A1 (de) 1972-12-07
GB1386821A (en) 1975-03-12
FR2138612B1 (enrdf_load_stackoverflow) 1973-07-13
CH565319A5 (enrdf_load_stackoverflow) 1975-08-15
AU3763272A (en) 1973-07-12
CA952820A (en) 1974-08-13

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