GB1080026A - Improvements relating to the fixing of turbine and compressor blades - Google Patents

Improvements relating to the fixing of turbine and compressor blades

Info

Publication number
GB1080026A
GB1080026A GB4332464A GB4332464A GB1080026A GB 1080026 A GB1080026 A GB 1080026A GB 4332464 A GB4332464 A GB 4332464A GB 4332464 A GB4332464 A GB 4332464A GB 1080026 A GB1080026 A GB 1080026A
Authority
GB
United Kingdom
Prior art keywords
blade
projections
wedge
clamping members
groove
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
GB4332464A
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 GB1080026A publication Critical patent/GB1080026A/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
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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

Landscapes

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

Abstract

1,080,026. Fixing turbine or compressor blades. SULZER BROS. Ltd. Oct. 23, 1964 [Nov. 1, 1963], No. 43324/64. Heading F1T. A turbine or compressor blade root is formed with outwardly facing surfaces clamped between the faces of two opposed projections which extend perpendicularly to the longitudinal axis of the blade and are formed on removable clamping members, the outwardly facing surfaces converging longitudinally of the blade so that the root is held between the projections by a wedging action, and the widths of the faces of the projections being substantially smaller than the widths of the outwardly facing surfaces, the widths being measured longitudinally of the blade. As shown, a stator blade 1 has a root comprising a wedge-shaped portion 12 and a threaded stud 2. Two clamping members 13, each having a part-cylindrical outside surface, are formed with inclined inner surfaces 15, which extend parallel to the inclined surfaces 12' of the wedge 12, and projections 14 which engage the surfaces 12'. The clamping members 13 are received in a bore 13' of a rectangular blade shoe 4 and secured therein, together with the blade, by a nut 3. The blade angle may be adjusted by temporarily backing-off the nut 3. The shoe 4 is positioned in a groove 5 in a blade support ring 6 by two pegs 7 which engage a groove 8 formed in one side of the groove 5, and is wedged against the other side of the groove 5 by wedges 11. Spacer shims 16 are provided between adjacent blade shoes. Alternative clamping members (not shown), have projections 14 located at different points of their inclined inner surfaces 15 so that the wedge 12 may be clamped at its widest point, its narrowest point, or any point therebetween. The natural frequency of vibration of the blades is thereby adjustable. An assembly for fixing a rotor blade, Fig. 6 (not shown), differs from the assembly shown in Figs. 1 and 2 in that the wedge tapers towards the aerofoil portion of the blade, and the blade is urged radially outwardly so that the inclined surfaces of the wedge abut the projections on the clamping members.
GB4332464A 1963-11-01 1964-10-23 Improvements relating to the fixing of turbine and compressor blades Expired GB1080026A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1352963A CH407165A (en) 1963-11-01 1963-11-01 Turbomachine blade

Publications (1)

Publication Number Publication Date
GB1080026A true GB1080026A (en) 1967-08-23

Family

ID=4393209

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4332464A Expired GB1080026A (en) 1963-11-01 1964-10-23 Improvements relating to the fixing of turbine and compressor blades

Country Status (6)

Country Link
BE (1) BE655002A (en)
CH (1) CH407165A (en)
DE (1) DE1283852B (en)
FR (1) FR1406928A (en)
GB (1) GB1080026A (en)
NL (2) NL300989A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1681472A1 (en) * 2005-01-14 2006-07-19 ALSTOM Technology Ltd Method for retrofitting a compressor
EP1707747A1 (en) * 2005-03-18 2006-10-04 Siemens Aktiengesellschaft Blade root fixation device and corresponding mounting method
EP3170982A1 (en) * 2015-11-19 2017-05-24 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH494341A (en) * 1968-07-26 1970-07-31 Sulzer Ag Rotor for turbo machinery
US3984194A (en) * 1974-04-12 1976-10-05 Aktiebolaget Svenska Flaktfabriken Axial flow fans
US4012171A (en) * 1974-04-24 1977-03-15 Suvak Michael N Blade and mounting means
US4047840A (en) * 1975-05-29 1977-09-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Impact absorbing blade mounts for variable pitch blades
US4007998A (en) * 1975-08-22 1977-02-15 Carrier Corporation Blade assembly
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1005530B (en) * 1955-06-23 1957-04-04 Paul Miesbeck Fastening of the rotor blades of centrifugal machines, in particular steam and gas turbines
DE1090370B (en) * 1959-01-20 1960-10-06 Sulzer Ag Blade attachment for an axial turbo machine
CH363754A (en) * 1959-01-20 1962-08-15 Sulzer Ag Blade attachment in an axial turbo machine
CH363358A (en) * 1959-01-29 1962-07-31 Sulzer Ag Blade attachment for an axial turbo machine

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1681472A1 (en) * 2005-01-14 2006-07-19 ALSTOM Technology Ltd Method for retrofitting a compressor
WO2006075014A1 (en) * 2005-01-14 2006-07-20 Alstom Technology Ltd Method for modifying a multistage compressor
US7753649B2 (en) 2005-01-14 2010-07-13 Alstom Technology Ltd. Method for modifying a multistage compressor
EP1707747A1 (en) * 2005-03-18 2006-10-04 Siemens Aktiengesellschaft Blade root fixation device and corresponding mounting method
EP3170982A1 (en) * 2015-11-19 2017-05-24 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US20170146020A1 (en) * 2015-11-19 2017-05-25 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
CN106930975A (en) * 2015-11-19 2017-07-07 通用电气公司 For the rotor assembly and the method for assembling that are used in fanjet
US10125619B2 (en) 2015-11-19 2018-11-13 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
CN106930975B (en) * 2015-11-19 2019-07-16 通用电气公司 Method for the rotor assembly used in fanjet and assembling

Also Published As

Publication number Publication date
BE655002A (en) 1965-04-29
FR1406928A (en) 1965-07-23
NL300989A (en) 1965-09-27
DE1283852B (en) 1968-11-28
NL123379C (en)
CH407165A (en) 1966-02-15

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