GB137379A - Improvements relating to turbine blades - Google Patents

Improvements relating to turbine blades

Info

Publication number
GB137379A
GB137379A GB120619A GB120619A GB137379A GB 137379 A GB137379 A GB 137379A GB 120619 A GB120619 A GB 120619A GB 120619 A GB120619 A GB 120619A GB 137379 A GB137379 A GB 137379A
Authority
GB
United Kingdom
Prior art keywords
blade
root
turbine blades
face
improvements relating
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
GB120619A
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.)
Vickers Ltd
Original Assignee
Vickers Ltd
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 Vickers Ltd filed Critical Vickers Ltd
Priority to GB120619A priority Critical patent/GB137379A/en
Publication of GB137379A publication Critical patent/GB137379A/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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

137,379. Vickers, Ltd., McKechnie, Sir J., and Johnson, G. W. Jan. 16, 1919. Blades &c.-In blade-fixine devices of the kind wherein the root c of the blade d having the spring section integrally connected therewith is formed so that it can be twisted into place in an undercut groove in the rotor or stator, the undercut groove a is made of inverted- T cross-section. The root c is formed on one face flush with the rear portion of the blade. while its other face is curved to conform with the convex face of the adjoining root.
GB120619A 1919-01-16 1919-01-16 Improvements relating to turbine blades Expired GB137379A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB120619A GB137379A (en) 1919-01-16 1919-01-16 Improvements relating to turbine blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB120619A GB137379A (en) 1919-01-16 1919-01-16 Improvements relating to turbine blades

Publications (1)

Publication Number Publication Date
GB137379A true GB137379A (en) 1920-01-15

Family

ID=9717988

Family Applications (1)

Application Number Title Priority Date Filing Date
GB120619A Expired GB137379A (en) 1919-01-16 1919-01-16 Improvements relating to turbine blades

Country Status (1)

Country Link
GB (1) GB137379A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4878811A (en) * 1988-11-14 1989-11-07 United Technologies Corporation Axial compressor blade assembly
EP0388286A1 (en) * 1989-03-15 1990-09-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Blades with hammer-type feet for improved angular positioning

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4878811A (en) * 1988-11-14 1989-11-07 United Technologies Corporation Axial compressor blade assembly
EP0388286A1 (en) * 1989-03-15 1990-09-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Blades with hammer-type feet for improved angular positioning
US5044886A (en) * 1989-03-15 1991-09-03 Societe Nationale D'etude Et De Moteurs D'aviation "S.N.E.C.M.A." Rotor blade fixing providing improved angular alignment of said blades

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