US2873088A - Lightweight rotor construction - Google Patents

Lightweight rotor construction Download PDF

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Publication number
US2873088A
US2873088A US356497A US35649753A US2873088A US 2873088 A US2873088 A US 2873088A US 356497 A US356497 A US 356497A US 35649753 A US35649753 A US 35649753A US 2873088 A US2873088 A US 2873088A
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Prior art keywords
blading
rim
disk
platform
rotor
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US356497A
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Neumann Gerhard
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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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like

Definitions

  • the present invention relates generally to turbomachines and more particularly to the platform filler structure between rotor blading of compressors, turbines and the like.
  • Blading used in such machines comes with either a wide blade base platform or a narrow blade base; with the former type a continuous circumferential surface is formed on the rotor disk periphery, while the bases of the latter type do not contact each other, so that the resulting gaps between adjacent blad-ing must be filled by platforms, which are part of the rotor disk rim, to form a substantially continuous surface.
  • the means of blading attachment such as a fir-tree or a dovetail construe tion or' rivets
  • the means of blading attachment are subjected to forces of considerable magnitude, due largely to the Weights of the blade airfoils and of the blade bases, especially in the former type.
  • the rotor disk rims suffer considerable high local stresses, caused by the use of integral platforms to fill the gaps between adjacent blading.
  • the object of my invention is to provide an improved rotor construction which is simpler and less expensive to manufacture and more readily repairable.
  • Another object of the invention is to provide an improved lightweight rotor which can be operated at higher speeds than conventional rotor structure.
  • Still another object of the invention is to provide an improved lightweight rotor structure which results in large economies in weight and use of critical materials.
  • a further object of the invention is to provide an improved lightweight rotor structure for a turbomachine in which the life of the blading is increased.
  • a still further object of the invention is to provide turbomachine blading with integral platforms produced with a great economy in machining time.
  • Another object of my invention is to provide a means for locating blading on a rotor disk without causing local high stress concentrations.
  • Fig. 1 is a partly exploded isometric view of my improved lightweight rotor structure
  • Fig. 2 is an isometric view of a modification of my sheet metal platform filler.
  • a section of a turbomachine is dis closed generally at 10, comprising a relatively lightweight, large diameter rotor disk 11, blading 12 and lightweight sheet metal platform spacers or filler pieces 13, held in assembled relationship by retaining wires 14 disposed on opposite sides of rotor disk 11.
  • the periphery or rim 11a of disk 11 carries grooves of either a fir-tree or dove-tail configuration, as shown at 15, to receive blading 12 having a base 12a with a form corresponding to the groove in the disk rim.
  • the width of the disk rim has been narrowed to be strong enough only to support the blading, lightweight platform fillers and retaining wires when in assembled relationship, so that the Web thickness of the disk also has been reduced accordingly, because of the lessened centrifugal stresses due to smaller rim weight.
  • Base 12a has two pairs of opposed surfaces 12d and 122 which define radially extending surfaces outlining the tenon or toe portion 12b and the substantially parallel faces of bases 12a.
  • the height of the surfaces 12c cause the top or platform 12 of base 12a to protrude beyond the rim 11a to the extent of the thickness of the sheetmetal platform spacers 13 to provide in assembled relationship therewith, a smooth aerodynamic platform outer surface between adjacent blading.
  • the two pairs of opposed surfaces 121; and 12c defir'le'a'xially extending faces which outline (l) the parallel faces 12d, adjacent the toe portion 12b, and (2) the outwardly flaring platform supporting faces 12c, each of which latter faces extend beyond the dimensions of the axial width of the rim 11a and which contain a semi-round groove 16 substantially parallel to the platform 12 of base 12a.
  • My preferred embodiment of platform filler i3 is constructed from a single piece of sheet metal bent inwardly away from platform surface 13a to form on the inner side thereof, substantially parallel channels 13b and wheel rim gripping flanges 13c, which are formed by 'reentrant bending of the ends of the sheet metal defining the channels and serve to hold the platform filler in position on the disk rim prior to final assembly of the lightweight rotor, which follows by the insertion of proper size retaining wires 14 through the channels 13b of the platform filler sections 13 and against the aligned grooves 16 in the base of the blades 12.
  • the flanges 13c13c span the rotor rim 11 so as to resiliently engage the sides of the wheel 11.
  • the retaining wires prevent radial spacer movement and provide a dampening action to increase the life of the blading.
  • the ends of the retaining wires are fastened together in some appropriate manner. When a retaining wire is removed for repairs of individual blading, it is replaced easily if damaged in removal. For better efficiency, the bent over edges of the fillers defining the leading and trailing edges thereof should approximate the corresponding edges of the outwardly flaring faces He.
  • the modification of the platform filler structure disclosed in Fig. 2 at 23 is a two piece, sheet metal structure comprising an outer parallelogram shaped platform section 23a welded to an inner section 23b similar in shape but formed with a pair of spaced parallel channels 23c for resilient mounting on the rotor and through which the retaining wires 14 are threaded to lock the blading 12 and platform fillers 23 in position on the disk rim, the bases of the blading 12 having grooves 16 as in the preferred embodiment.
  • a platform filler for a rotor having blading spaced on the rim thereof comprising a sheet metal plane section defining an aerodynamic surface adapted to be inserted between adjacent blading and a pair of spaced channels on the opposing surface thereof, the ends of said plane section defining said channels comprising re-entrant flanges adapted to resiliently engage said rim.
  • An integrated sheet metal platform filler for a rotor disk having a grooved rim carrying insertable blading comprising an outer plane section adapted to be inserted between adjacent blading for forming a smooth aerodynamic surface therebetween and an inner section having spaced grooves thereon joined to said plane section and forming channels therewith, said channels adapted to span said rotor disk when said filler is in operative position.
  • a rotor disk, blading and platform fillers having a smooth outer surface thereon, said disk having a relatively large diameter and a relatively narrow rim, said blading being attached to said rim and having a platform portion extending beyond the periphery thereof, and said platform fillers being disposed between said blading and fastened thereto by locking means extending around the periphery of said disk, said fillers thereby forming an aerodynamic surface between said blading, said fillers having resilient faces engaging opposite sides of the rotor disk rim.
  • a lightweight rimmed rotor the combination of a disk having spaced apart peripheral grooves extending across the width of the rim of said disk, blading having a base portion disposed in said grooves, said base portion having substantially parallel semi-round grooves located on opposite sides of the rim of said disk when in assembled relationship therewith, and filler pieces between said blading in close abutting relationship therewith to form smooth flow surfaces, said filler pieces having channels on their inner sides separated by the rim of said disk, the inner sides of said channels having re-entrant portions in resilient engagement with said rim, and means for fastening said blading and filler pieces to said disk comprising a retaining wire through said channels and engaging said base grooves.
  • a turbomachine having a peripheral grooved rotor disk with insertable blading disposed in the grooves of said disk, said blading having bases containing semiround grooves, separably removable spacing members fitting between adjacent blading on the periphery of said disk and forming an outer aerodynamic surface therewith, the spacing members having substantially parallel channels formed on the inner surfaces thereof, in combination with annular fastening means threaded through each of said channels and engaging the grooves in the bases of said blading to form an integrated assembly.

Description

e 1 1 G. NEUMANN 2,873,088.
LIGHTWEIGHT ROTOR CONSTRUCTION Filed May 21. 1953 Inventor: G erharci N egmann,
His Attorney.
Uni-Ed StfltS Patent 2,873,088 LIGHTWEIGHT ROTOR CONSTRUCTION Gerhard Neumarin, Cincinnati, Ohio, assignor toGeneral Electric Company, a corporation of New. York Application May 21, 1953, Serial No. 356,497
' 7Claims. Cl. 253-77 'The present invention relates generally to turbomachines and more particularly to the platform filler structure between rotor blading of compressors, turbines and the like.
Blading used in such machines comes with either a wide blade base platform or a narrow blade base; with the former type a continuous circumferential surface is formed on the rotor disk periphery, while the bases of the latter type do not contact each other, so that the resulting gaps between adjacent blad-ing must be filled by platforms, which are part of the rotor disk rim, to form a substantially continuous surface.
During operation of the machines, the means of blading attachment, such as a fir-tree or a dovetail construe tion or' rivets, are subjected to forces of considerable magnitude, due largely to the Weights of the blade airfoils and of the blade bases, especially in the former type. When narrow base blading is used, the rotor disk rims suffer considerable high local stresses, caused by the use of integral platforms to fill the gaps between adjacent blading.
The forces and stresses in rotor disks due to high speed of rotation are decreased considerably by reducing the weight of the blade with integral platform, which in turn results in a reduction of disk rim Web thickness, or by reducing the rim width and by eliminating the disk platform structure.
Furthermore, stresses within the blading are reduced considerably by a more elastic installation of bladirig in the disk rim and introduction of dampening action from the locking means used. j
The object of my invention is to provide an improved rotor construction which is simpler and less expensive to manufacture and more readily repairable.
Another object of the invention is to provide an improved lightweight rotor which can be operated at higher speeds than conventional rotor structure.
Still another object of the invention is to provide an improved lightweight rotor structure which results in large economies in weight and use of critical materials.
A further object of the invention is to provide an improved lightweight rotor structure for a turbomachine in which the life of the blading is increased.
A still further object of the invention is to provide turbomachine blading with integral platforms produced with a great economy in machining time.
Another object of my invention is to provide a means for locating blading on a rotor disk without causing local high stress concentrations.
These and other objects of the invention will become more apparent by reference to the following description taken in conjunction with the accompanying drawing, which illustrates preferred embodiments of my invention and in which:
Fig. 1 is a partly exploded isometric view of my improved lightweight rotor structure; and
Fig. 2 is an isometric view of a modification of my sheet metal platform filler.
2,873,088 Patented Feb. 10, 1959 In accordance with the illustrated embodiments of my disclosure, I accomplish the objects of my invention by replacing heavy metallic blade or rotor disk platform structures with separate sheet metal platform fillers.
In the drawing, a section of a turbomachine is dis closed generally at 10, comprising a relatively lightweight, large diameter rotor disk 11, blading 12 and lightweight sheet metal platform spacers or filler pieces 13, held in assembled relationship by retaining wires 14 disposed on opposite sides of rotor disk 11.
The periphery or rim 11a of disk 11, carries grooves of either a fir-tree or dove-tail configuration, as shown at 15, to receive blading 12 having a base 12a with a form corresponding to the groove in the disk rim. The width of the disk rim has been narrowed to be strong enough only to support the blading, lightweight platform fillers and retaining wires when in assembled relationship, so that the Web thickness of the disk also has been reduced accordingly, because of the lessened centrifugal stresses due to smaller rim weight.
Base 12a has two pairs of opposed surfaces 12d and 122 which define radially extending surfaces outlining the tenon or toe portion 12b and the substantially parallel faces of bases 12a. The height of the surfaces 12c cause the top or platform 12 of base 12a to protrude beyond the rim 11a to the extent of the thickness of the sheetmetal platform spacers 13 to provide in assembled relationship therewith, a smooth aerodynamic platform outer surface between adjacent blading. The two pairs of opposed surfaces 121; and 12c defir'le'a'xially extending faces which outline (l) the parallel faces 12d, adjacent the toe portion 12b, and (2) the outwardly flaring platform supporting faces 12c, each of which latter faces extend beyond the dimensions of the axial width of the rim 11a and which contain a semi-round groove 16 substantially parallel to the platform 12 of base 12a.
My preferred embodiment of platform filler i3 is constructed from a single piece of sheet metal bent inwardly away from platform surface 13a to form on the inner side thereof, substantially parallel channels 13b and wheel rim gripping flanges 13c, which are formed by 'reentrant bending of the ends of the sheet metal defining the channels and serve to hold the platform filler in position on the disk rim prior to final assembly of the lightweight rotor, which follows by the insertion of proper size retaining wires 14 through the channels 13b of the platform filler sections 13 and against the aligned grooves 16 in the base of the blades 12. The flanges 13c13c span the rotor rim 11 so as to resiliently engage the sides of the wheel 11. In this manner, not only are the blades connected to the sections or spacers 13 and locked in position and prevented from moving axially but the retaining wires prevent radial spacer movement and provide a dampening action to increase the life of the blading. The ends of the retaining wires are fastened together in some appropriate manner. When a retaining wire is removed for repairs of individual blading, it is replaced easily if damaged in removal. For better efficiency, the bent over edges of the fillers defining the leading and trailing edges thereof should approximate the corresponding edges of the outwardly flaring faces He.
The modification of the platform filler structure disclosed in Fig. 2 at 23 is a two piece, sheet metal structure comprising an outer parallelogram shaped platform section 23a welded to an inner section 23b similar in shape but formed with a pair of spaced parallel channels 23c for resilient mounting on the rotor and through which the retaining wires 14 are threaded to lock the blading 12 and platform fillers 23 in position on the disk rim, the bases of the blading 12 having grooves 16 as in the preferred embodiment.
It will be apparent to those skilled in the art that 3 applicants novel rotor is of lightweight construction having a reduced rim width and web thickness, that lighter blading is required with the use of sheet metal platform spacers, that blade life is increased by more elastic mounting, and that repairs are greatly facilitated.
What I claim as new and desire to secure by Letters Patent of the United States is:
1. A platform filler for a rotor having blading spaced on the rim thereof, said filler comprising a sheet metal plane section defining an aerodynamic surface adapted to be inserted between adjacent blading and a pair of spaced channels on the opposing surface thereof, the ends of said plane section defining said channels comprising re-entrant flanges adapted to resiliently engage said rim.
2. A sheet metal platform filler for a rotor disk having rim spaced blading and comprising a plane section adapted to be inserted between adjacent blading thereby forming an aerodynamic surface therewith, a pair of spaced channels extending inwardly away from said plane section and adapted to span said rotor, the inner edges of the walls of said channels having re-entrant portions adapted to receive the rim portion of said disk between them whereby axial movement of said filler is restrained.
3. An integrated sheet metal platform filler for a rotor disk having a grooved rim carrying insertable blading comprising an outer plane section adapted to be inserted between adjacent blading for forming a smooth aerodynamic surface therebetween and an inner section having spaced grooves thereon joined to said plane section and forming channels therewith, said channels adapted to span said rotor disk when said filler is in operative position.
4. In combination, a rotor disk, blading and platform fillers having a smooth outer surface thereon, said disk having a relatively large diameter and a relatively narrow rim, said blading being attached to said rim and having a platform portion extending beyond the periphery thereof, and said platform fillers being disposed between said blading and fastened thereto by locking means extending around the periphery of said disk, said fillers thereby forming an aerodynamic surface between said blading, said fillers having resilient faces engaging opposite sides of the rotor disk rim.
5. In combination with a rimmed rotor disk having circumferentially spaced apart grooves in the rim portion and blading provided with bases which correspond in form to said grooves for fastening said blading to said rim, sheet metal platform fillers disposed between said blading having a platform section extending beyond the periphery of said disk when in operative position, said platform fillers being attached to the blading providing an aerodynamic surface therebetween and having channels on the surface opposite thereto and spaced to span the rim of said disk in resilient engagement therewith, said blading having parallel grooves on the base of said blading substantially in alignment with said channels, and means interconnecting said fillers and blading passing through said channels and engaging said grooves to form an integrated assembly.
6. In a lightweight rimmed rotor, the combination of a disk having spaced apart peripheral grooves extending across the width of the rim of said disk, blading having a base portion disposed in said grooves, said base portion having substantially parallel semi-round grooves located on opposite sides of the rim of said disk when in assembled relationship therewith, and filler pieces between said blading in close abutting relationship therewith to form smooth flow surfaces, said filler pieces having channels on their inner sides separated by the rim of said disk, the inner sides of said channels having re-entrant portions in resilient engagement with said rim, and means for fastening said blading and filler pieces to said disk comprising a retaining wire through said channels and engaging said base grooves.
7. In a turbomachine having a peripheral grooved rotor disk with insertable blading disposed in the grooves of said disk, said blading having bases containing semiround grooves, separably removable spacing members fitting between adjacent blading on the periphery of said disk and forming an outer aerodynamic surface therewith, the spacing members having substantially parallel channels formed on the inner surfaces thereof, in combination with annular fastening means threaded through each of said channels and engaging the grooves in the bases of said blading to form an integrated assembly.
References Cited in the file of this patent UNITED STATES PATENTS
US356497A 1953-05-21 1953-05-21 Lightweight rotor construction Expired - Lifetime US2873088A (en)

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Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000612A (en) * 1960-04-18 1961-09-19 Napier & Son Ltd Turbine blade rings and methods of assembly
US3183734A (en) * 1961-06-10 1965-05-18 Sedis Transmissions Mec Toothed wheel
US3515501A (en) * 1967-04-12 1970-06-02 Rolls Royce Rotor blade assembly
US3881844A (en) * 1974-05-28 1975-05-06 Gen Electric Blade platform vibration dampers
EP0084491A1 (en) * 1982-01-14 1983-07-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Axial locking of rotor blades for turbines and compressors
US4482297A (en) * 1981-11-16 1984-11-13 Terry Corporation Bladed rotor assembly
US4995788A (en) * 1989-09-08 1991-02-26 United Technologies Corporation Composite rotor blade
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
US5022825A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pitch retention member
US5049035A (en) * 1988-11-23 1991-09-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Bladed disc for a turbomachine rotor
FR2660363A1 (en) * 1990-04-03 1991-10-04 Gen Electric STRUCTURE FOR FIXING THE INTERNAL END OF A TURBINE BLADE.
US5102300A (en) * 1988-10-07 1992-04-07 United Technologies Corporation Pinned airfoil propeller assembly
US5193982A (en) * 1991-07-17 1993-03-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Separate inter-blade platform for a bladed rotor disk
US6082970A (en) * 1997-05-26 2000-07-04 Ishikawajima-Harima Heavy Industries Co., Ltd. Vibration attenuation arrangement for rotor blades
WO2000057032A1 (en) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Guide blade and guide blade rim for a fluid-flow machine and component for delimiting a flow channel
US6533550B1 (en) 2001-10-23 2003-03-18 Pratt & Whitney Canada Corp. Blade retention
US20050254958A1 (en) * 2004-05-14 2005-11-17 Paul Stone Natural frequency tuning of gas turbine engine blades
US20050265847A1 (en) * 2004-05-28 2005-12-01 Rolls-Royce Plc Rotor assembly and annulus filler for gas turbine engine compressor
US20120087798A1 (en) * 2010-10-06 2012-04-12 General Electric Company Turbine bucket lockwire rotation prevention
EP2818638A1 (en) * 2013-06-27 2014-12-31 MTU Aero Engines GmbH Rotor-blade group, method and turbomachine
US20150176419A1 (en) * 2012-07-27 2015-06-25 Snecma Part to modify the profile of an aerodynamic jet
US20160069188A1 (en) * 2014-09-05 2016-03-10 United Technologies Corporation Gas turbine engine airfoil structure
US20160177760A1 (en) * 2014-12-18 2016-06-23 General Electric Technology Gmbh Gas turbine vane
US20160238021A1 (en) * 2015-02-16 2016-08-18 United Technologies Corporation Compressor Airfoil
CN113464464A (en) * 2020-03-31 2021-10-01 通用电气公司 Turbine circumferential dovetail leakage reduction

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Publication number Priority date Publication date Assignee Title
US1585713A (en) * 1922-05-31 1926-05-25 Westinghouse Electric & Mfg Co Turbine-blade fastening
US2279258A (en) * 1939-05-08 1942-04-07 Allis Chalmers Mfg Co Turbine blading
US2415847A (en) * 1943-05-08 1947-02-18 Westinghouse Electric Corp Compressor apparatus
US2559013A (en) * 1946-01-25 1951-07-03 United Specialties Co Method of making turbine wheels
FR989556A (en) * 1949-06-25 1951-09-11 Cem Comp Electro Mec Improvement in turbo-machine blades
FR989839A (en) * 1949-06-28 1951-09-13 Cem Comp Electro Mec Blade for turbo-machine
US2649278A (en) * 1948-07-15 1953-08-18 Edward A Stalker Rotor construction for fluid machines
US2656146A (en) * 1948-04-08 1953-10-20 Curtiss Wright Corp Turbine blade construction
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
US2713991A (en) * 1951-05-05 1955-07-26 A V Roe Canada Ltd Rotor blade locking device
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1585713A (en) * 1922-05-31 1926-05-25 Westinghouse Electric & Mfg Co Turbine-blade fastening
US2279258A (en) * 1939-05-08 1942-04-07 Allis Chalmers Mfg Co Turbine blading
US2415847A (en) * 1943-05-08 1947-02-18 Westinghouse Electric Corp Compressor apparatus
US2559013A (en) * 1946-01-25 1951-07-03 United Specialties Co Method of making turbine wheels
US2656146A (en) * 1948-04-08 1953-10-20 Curtiss Wright Corp Turbine blade construction
US2649278A (en) * 1948-07-15 1953-08-18 Edward A Stalker Rotor construction for fluid machines
FR989556A (en) * 1949-06-25 1951-09-11 Cem Comp Electro Mec Improvement in turbo-machine blades
FR989839A (en) * 1949-06-28 1951-09-13 Cem Comp Electro Mec Blade for turbo-machine
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
US2713991A (en) * 1951-05-05 1955-07-26 A V Roe Canada Ltd Rotor blade locking device

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000612A (en) * 1960-04-18 1961-09-19 Napier & Son Ltd Turbine blade rings and methods of assembly
US3183734A (en) * 1961-06-10 1965-05-18 Sedis Transmissions Mec Toothed wheel
US3515501A (en) * 1967-04-12 1970-06-02 Rolls Royce Rotor blade assembly
US3881844A (en) * 1974-05-28 1975-05-06 Gen Electric Blade platform vibration dampers
DE2503513A1 (en) * 1974-05-28 1975-12-11 Gen Electric VIBRATION DAMPER FOR TURBINE BLADE PLATFORMS
US4482297A (en) * 1981-11-16 1984-11-13 Terry Corporation Bladed rotor assembly
EP0084491A1 (en) * 1982-01-14 1983-07-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Axial locking of rotor blades for turbines and compressors
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
US5022825A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pitch retention member
US5102300A (en) * 1988-10-07 1992-04-07 United Technologies Corporation Pinned airfoil propeller assembly
US5049035A (en) * 1988-11-23 1991-09-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Bladed disc for a turbomachine rotor
US4995788A (en) * 1989-09-08 1991-02-26 United Technologies Corporation Composite rotor blade
FR2660363A1 (en) * 1990-04-03 1991-10-04 Gen Electric STRUCTURE FOR FIXING THE INTERNAL END OF A TURBINE BLADE.
US5193982A (en) * 1991-07-17 1993-03-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Separate inter-blade platform for a bladed rotor disk
US6082970A (en) * 1997-05-26 2000-07-04 Ishikawajima-Harima Heavy Industries Co., Ltd. Vibration attenuation arrangement for rotor blades
WO2000057032A1 (en) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Guide blade and guide blade rim for a fluid-flow machine and component for delimiting a flow channel
US6632070B1 (en) 1999-03-24 2003-10-14 Siemens Aktiengesellschaft Guide blade and guide blade ring for a turbomachine, and also component for bounding a flow duct
US6533550B1 (en) 2001-10-23 2003-03-18 Pratt & Whitney Canada Corp. Blade retention
US20050254958A1 (en) * 2004-05-14 2005-11-17 Paul Stone Natural frequency tuning of gas turbine engine blades
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US7527476B2 (en) * 2004-05-28 2009-05-05 Rolls-Royce Plc Rotor assembly and annulus filler for gas turbine engine compressor
US20050265847A1 (en) * 2004-05-28 2005-12-01 Rolls-Royce Plc Rotor assembly and annulus filler for gas turbine engine compressor
US20120087798A1 (en) * 2010-10-06 2012-04-12 General Electric Company Turbine bucket lockwire rotation prevention
US8905717B2 (en) * 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
US9982546B2 (en) * 2012-07-27 2018-05-29 Snecma Part to modify the profile of an aerodynamic jet
US20150176419A1 (en) * 2012-07-27 2015-06-25 Snecma Part to modify the profile of an aerodynamic jet
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