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GB1192159A - Blades for Turbomachines - Google Patents

Blades for Turbomachines

Info

Publication number
GB1192159A
GB1192159A GB04991/69A GB1499169A GB1192159A GB 1192159 A GB1192159 A GB 1192159A GB 04991/69 A GB04991/69 A GB 04991/69A GB 1499169 A GB1499169 A GB 1499169A GB 1192159 A GB1192159 A GB 1192159A
Authority
GB
United Kingdom
Prior art keywords
root portion
clamping ring
collar
blade
root
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB04991/69A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sulzer AG
Original Assignee
Sulzer AG
Gebrueder Sulzer AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Sulzer AG, Gebrueder Sulzer AG filed Critical Sulzer AG
Publication of GB1192159A publication Critical patent/GB1192159A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,192,159. Turbines; axial flow compressors and pumps. SULZER BROS. Ltd. March 21, 1969 [March 26, 1968], No. 14991/69. Headings F1C and F1T. A rotor or stator blade for a turbine, compressor or pump comprises an aerofoil portion 12 and a root portion 11 retained within a cylindrical bore 22 in a root part 23 by a nut 24 screwed on to the root portion and engaging a wedging device. The latter comprises a clamping ring 19À1 fitting over a cylindrical surface 13 of the root portion 11 to engage a plane surface 16 normal to the axis of the surface 13. The external surface 20 of the ring 19À1 is tapered and is engaged by a corresponding tapered bore in a collar 21. Thus when nut 24 is tightened against collar 21, the root portion 11 is wedged in any desired angular position within part 23. The latter is shaped for insertion in a radial hole or transverse groove in the rotor or stator. The natural vibration frequency of the blade can be altered by fitting a different clamping ring (19À2), Fig. 2 (not shown), which instead of engaging plane surface 16 engages a similar surface 17 adjacent the aerofoil portion 12. An inspection hole 26 is provided for examination of the clamping ring. The approximate natural frequency of the blade is initially set by machining a groove 25 in the root portion 11. The clamping ring 19À1 and the collar 21 may each be slit or divided circumferentially into at least two parts.
GB04991/69A 1968-03-26 1969-03-21 Blades for Turbomachines Expired GB1192159A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH446168A CH488939A (en) 1968-03-26 1968-03-26 Bucket for turbo machinery

Publications (1)

Publication Number Publication Date
GB1192159A true GB1192159A (en) 1970-05-20

Family

ID=4276544

Family Applications (1)

Application Number Title Priority Date Filing Date
GB04991/69A Expired GB1192159A (en) 1968-03-26 1969-03-21 Blades for Turbomachines

Country Status (6)

Country Link
US (1) US3521974A (en)
BE (1) BE730456A (en)
CH (1) CH488939A (en)
FR (1) FR2004710A1 (en)
GB (1) GB1192159A (en)
NL (1) NL6805582A (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012171A (en) * 1974-04-24 1977-03-15 Suvak Michael N Blade and mounting means
US4245954A (en) * 1978-12-01 1981-01-20 Westinghouse Electric Corp. Ceramic turbine stator vane and shroud support
GB2234299B (en) * 1989-07-06 1994-01-05 Rolls Royce Plc Mounting system for engine components having dissimilar coefficients of thermal expansion
GB2278647B (en) * 1990-12-27 1995-04-05 Snecma Method of fixing flow-straightening blades in a turboshaft engine
FR2671133B1 (en) * 1990-12-27 1994-10-21 Snecma RAPIDLY FIXED PIVOT BLADE FOR TURBOMACHINE RECTIFIER BLADE AND METHOD FOR FIXING SAID BLADE.
US6435821B1 (en) * 2000-12-20 2002-08-20 United Technologies Corporation Variable vane for use in turbo machines
US8092165B2 (en) * 2008-01-21 2012-01-10 Pratt & Whitney Canada Corp. HP segment vanes
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
IT1393757B1 (en) * 2008-07-28 2012-05-08 Ansaldo Energia Spa CONNECTION GROUP TO CONNECT A PALLET TO A SUPPORT RING, IN PARTICULAR TO AN INTERNAL RING OF A COMPRESSOR STATOR
US8485784B2 (en) * 2009-07-14 2013-07-16 General Electric Company Turbine bucket lockwire rotation prevention
DE102009047006A1 (en) * 2009-11-23 2011-05-26 Robert Bosch Gmbh charging
BE1023290B1 (en) * 2015-07-22 2017-01-24 Safran Aero Boosters S.A. AUBE COMPOSITE COMPRESSOR OF AXIAL TURBOMACHINE
FR3127533A1 (en) * 2021-09-28 2023-03-31 Safran Aircraft Engines Wedging system for articulated turbomachine blade, turbomachine blade equipped with this wedging system and method of mounting such wedging system on an articulated blade

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE724793C (en) * 1940-04-16 1942-09-05 Sulzer Ag Conveyor machine with mainly axially acting blades
US2955799A (en) * 1957-02-11 1960-10-11 United Aircraft Corp Blade damping means

Also Published As

Publication number Publication date
FR2004710A1 (en) 1969-11-28
CH488939A (en) 1970-04-15
US3521974A (en) 1970-07-28
NL6805582A (en) 1969-09-30
BE730456A (en) 1969-09-26

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees