GB817660A - Improvements in or relating to blades for gas turbines - Google Patents

Improvements in or relating to blades for gas turbines

Info

Publication number
GB817660A
GB817660A GB1546455A GB1546455A GB817660A GB 817660 A GB817660 A GB 817660A GB 1546455 A GB1546455 A GB 1546455A GB 1546455 A GB1546455 A GB 1546455A GB 817660 A GB817660 A GB 817660A
Authority
GB
United Kingdom
Prior art keywords
blank
slot
root
blade
forged
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
GB1546455A
Inventor
Cuthbert Marklew Tunstall
Thomas Greaves Wright
William Samuel Pollinger
Basil Davenport Blackwell
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 Aero Engines Ltd
Original Assignee
Bristol Aero Engines Ltd
Filing date
Publication date
Application filed by Bristol Aero Engines Ltd filed Critical Bristol Aero Engines Ltd
Priority to US586601A priority Critical patent/US2830357A/en
Priority to FR1154121D priority patent/FR1154121A/en
Publication of GB817660A publication Critical patent/GB817660A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Forging (AREA)

Abstract

817,660. Making gas - turbine blades. BRISTOL AERO-ENGINES Ltd. May 22, 1956 [May 27, 1955], No. 15464/55. Class 83 (2). A gas-turbine blade having an aerofoil working portion 2 with longitudinal cooling passages 7-10, a platform part 1, and a root portion 3 with abutment shoulders 5, is made from a blank having at least at one end a cross-section corresponding to that of the platform part and having longitudinal passages 8, Fig. 2, extending therethrough, and the root portion of the blade is formed by cutting an open-ended slot 12 in the said one end of the blank, forging the blank to press the prongs 16, 17 thus formed into contact with one another along the line 18, and then machining the end of the blank to the desired root form, the dimensions and position of the slot 12 being such that none of the cooling passages 7-10 in the finished blade break through any of the abutments 5 in the root. The blank may be formed by extrusion with four longitudinal passages 7-10, Fig. 1, disposed on an arc. The sides 31, 32 of the slot 12 extend tangentially to the holes 8 and 7, 10 respectively. After machining the root 3, the aerofoil portion 2 is machined and, if required, a shroud may be provided at the tip of the blade. The transverse passage 19 formed by closing of the prongs may be closed at one end to provide an inlet passage for cooling fluid ; alternatively it may be closed at both ends and in this case ports such as 8a are drilled. The blank may alternatively be formed by forging in which case the blade portion may be rough forged to aerofoil shape and subsequently machined, or may be precision forged so as to require final polishing only. The root portion of a forged or extruded blank may be forged before cutting the slot 12 to flatten the arc containing the cooling passages 7-10 and thus reduce the required width of the slot. In another embodiment, Figs. 4, 5 (not shown), the slot 12 is of V-section. The root may be formed with its abutments 5 parallel with the junction plane 18 of the prongs Fig. 3, or with the abutments extending perpendicular to this plane. In the latter case the abutment may lie along large radius arcs to suit the curvature of the rotor disc into which the blades are fitted.
GB1546455A 1955-05-27 1955-05-27 Improvements in or relating to blades for gas turbines Expired GB817660A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US586601A US2830357A (en) 1955-05-27 1956-05-22 Blades for gas turbines
FR1154121D FR1154121A (en) 1955-05-27 1956-05-25 Improvements in the manufacture of fins for gas turbines

Publications (1)

Publication Number Publication Date
GB817660A true GB817660A (en) 1959-08-06

Family

ID=1731540

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1546455A Expired GB817660A (en) 1955-05-27 1955-05-27 Improvements in or relating to blades for gas turbines

Country Status (1)

Country Link
GB (1) GB817660A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4692976A (en) * 1985-07-30 1987-09-15 Westinghouse Electric Corp. Method of making scalable side entry turbine blade roots
EP1174210A2 (en) * 2000-07-20 2002-01-23 MAN Turbomaschinen AG GHH BORSIG Method and blank for manufacturing rhomboidal blades for axial-flow fluid machines
EP1481756A1 (en) * 2003-05-27 2004-12-01 Snecma Moteurs Method of fabricating a hollow turbine blade
WO2005005785A1 (en) * 2003-07-12 2005-01-20 Alstom Technology Ltd Cooled blade for a gas turbine
CN104842129A (en) * 2015-03-30 2015-08-19 北京机电研究所 Precise blade extrusion forming method for combustion gas turbine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4692976A (en) * 1985-07-30 1987-09-15 Westinghouse Electric Corp. Method of making scalable side entry turbine blade roots
EP1174210A2 (en) * 2000-07-20 2002-01-23 MAN Turbomaschinen AG GHH BORSIG Method and blank for manufacturing rhomboidal blades for axial-flow fluid machines
EP1174210A3 (en) * 2000-07-20 2003-05-07 MAN Turbomaschinen AG Method and blank for manufacturing rhomboidal blades for axial-flow fluid machines
US6910270B2 (en) 2000-07-20 2005-06-28 Man Turbo Ag Process for preparing rhomboidal blades for axial turbo engines
CZ297900B6 (en) * 2000-07-20 2007-04-25 Man Turbo Ag Process for producing rhomboid blades of axial flow machines and a blank for this production process
EP1481756A1 (en) * 2003-05-27 2004-12-01 Snecma Moteurs Method of fabricating a hollow turbine blade
FR2855439A1 (en) * 2003-05-27 2004-12-03 Snecma Moteurs PROCESS FOR THE MANUFACTURE OF A HOLLOW BLADE FOR A TURBOMACHINE.
US7334332B2 (en) 2003-05-27 2008-02-26 Snecma Moteurs Method of manufacturing a hollow blade for a turbine engine
WO2005005785A1 (en) * 2003-07-12 2005-01-20 Alstom Technology Ltd Cooled blade for a gas turbine
US7264445B2 (en) 2003-07-12 2007-09-04 Alstom Technology Ltd Cooled blade or vane for a gas turbine
CN104842129A (en) * 2015-03-30 2015-08-19 北京机电研究所 Precise blade extrusion forming method for combustion gas turbine

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