GB722458A - Improvements in or relating to the manufacture of blades for use in axial flow compressors or the like - Google Patents

Improvements in or relating to the manufacture of blades for use in axial flow compressors or the like

Info

Publication number
GB722458A
GB722458A GB1776352A GB1776352A GB722458A GB 722458 A GB722458 A GB 722458A GB 1776352 A GB1776352 A GB 1776352A GB 1776352 A GB1776352 A GB 1776352A GB 722458 A GB722458 A GB 722458A
Authority
GB
United Kingdom
Prior art keywords
blank
root
blades
opening
blade
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
GB1776352A
Inventor
Bernard Sidney Massey
Stanley Clifford Warner
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.)
Bristol Aeroplane Co Ltd
Original Assignee
Bristol Aeroplane Co 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 Bristol Aeroplane Co Ltd filed Critical Bristol Aeroplane Co Ltd
Priority to GB1776352A priority Critical patent/GB722458A/en
Publication of GB722458A publication Critical patent/GB722458A/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces

Landscapes

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

Abstract

722,458. Compressor blades. BRISTOL AEROPLANE CO., Ltd. July 6, 1953 [July 14, 1952], No. 17763/52. Class 110 (3). [Also in Group XXII] In the manufacture of axial-flow compressor and like blades, the aerofoil blade blank 13 is formed separate from the root member 14 and is secured thereto by inserting an end portion of the blank into an opening 18 in the root member and then permanently deforming the latter so as to firmly grip the blade blank. Shallow recesses 20 are preferably formed in the blank to receive the displaced material of the root and form a key. The opening 18 is also enlarged at 19 and after deforming the root, the end of the blank is peened to fill the enlargement. The root member, which may be a die casting or forging consists of a plate 16 with a raised boss 17 surrounding the opening; the boss only is deformed for securing the blank therein and this deformation may be performed hot or cold. If the root member is of a harder metal, such as steel, than the blade blank, which may be of an aluminium-copper alloy, the pre-formed recesses 20 may be omitted since the material of the blank is sufficiently malleable to be indented by the root member during its deformation. A synthetic resin adhesive may be applied to the end of the blank and/or the opening in the root, which resin may be cold setting or be subsequently cured by heat treatment. The aerofoil blank may be made of high-tensile aluminiumcopper alloys, steel alloys or asbestos-resin plastic compositions and may be cut from rolled or extruded strip. The blades are mounted in peripheral grooves 12 in the compressor casing 11 by half rings 15 which have apertures 22 for passing over the blade blanks and which are secured to the casing by bolts 25.
GB1776352A 1952-07-14 1952-07-14 Improvements in or relating to the manufacture of blades for use in axial flow compressors or the like Expired GB722458A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1776352A GB722458A (en) 1952-07-14 1952-07-14 Improvements in or relating to the manufacture of blades for use in axial flow compressors or the like

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1776352A GB722458A (en) 1952-07-14 1952-07-14 Improvements in or relating to the manufacture of blades for use in axial flow compressors or the like

Publications (1)

Publication Number Publication Date
GB722458A true GB722458A (en) 1955-01-26

Family

ID=10100793

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1776352A Expired GB722458A (en) 1952-07-14 1952-07-14 Improvements in or relating to the manufacture of blades for use in axial flow compressors or the like

Country Status (1)

Country Link
GB (1) GB722458A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2522362A1 (en) * 1982-02-26 1983-09-02 Gen Electric BUILDING ELEMENT OF AUBES
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it
FR2654463A1 (en) * 1989-11-15 1991-05-17 Snecma TURBOMACHINE STATOR ELEMENT.
FR2680384A1 (en) * 1991-08-13 1993-02-19 Plastiremo Vane ring with simplified assembly, and vane for producing it

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2522362A1 (en) * 1982-02-26 1983-09-02 Gen Electric BUILDING ELEMENT OF AUBES
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it
FR2654463A1 (en) * 1989-11-15 1991-05-17 Snecma TURBOMACHINE STATOR ELEMENT.
EP0433111A1 (en) * 1989-11-15 1991-06-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Element of the stator of a turbo machine
US5083900A (en) * 1989-11-15 1992-01-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbomachine stator element
FR2680384A1 (en) * 1991-08-13 1993-02-19 Plastiremo Vane ring with simplified assembly, and vane for producing it

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