GB1119617A - Compressor blade for a gas turbine engine - Google Patents

Compressor blade for a gas turbine engine

Info

Publication number
GB1119617A
GB1119617A GB21758/66A GB2175866A GB1119617A GB 1119617 A GB1119617 A GB 1119617A GB 21758/66 A GB21758/66 A GB 21758/66A GB 2175866 A GB2175866 A GB 2175866A GB 1119617 A GB1119617 A GB 1119617A
Authority
GB
United Kingdom
Prior art keywords
blade
pieces
welding
joining
electron beam
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
GB21758/66A
Inventor
John Michael Storer Keen
Gordon Cyril May
Albert James Moreton
James Alexander Petrie
Frank Littleford
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB21758/66A priority Critical patent/GB1119617A/en
Priority to US636979A priority patent/US3524712A/en
Priority to DE19671628365 priority patent/DE1628365A1/en
Publication of GB1119617A publication Critical patent/GB1119617A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Welding Or Cutting Using Electron Beams (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,119,617. Making turbine blades; welding by fusion; welding by pressure. ROLLSROYCE Ltd. 5 May, 1967 [17 May, 1966], No. 21758/66. Headings B3A and B3R. [Also in Division F1] A method of making a clappered compressor blade 16 having an aerofoil working section made up of at least two pieces joined together along a surface extending across the blade and crossing the longest axis of the blade, comprises the steps of forgirg the pieces, such as 17, 18, 19 and 20, machining the surfaces to be joined and then electron beam welding or diffusion bonding the pieces together. In a modification, Fig. 3 (not shown), the radially outer piece (22) of the blade is hollow and formed from two flank portions electron beam welded together. The blade pieces may be forged oversize at the surfaces where joining is to take place, the surplus material being machined off after joining. The blade material may be steel or titanium.
GB21758/66A 1966-05-17 1966-05-17 Compressor blade for a gas turbine engine Expired GB1119617A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB21758/66A GB1119617A (en) 1966-05-17 1966-05-17 Compressor blade for a gas turbine engine
US636979A US3524712A (en) 1966-05-17 1967-05-08 Compressor blade for a gas turbine engine
DE19671628365 DE1628365A1 (en) 1966-05-17 1967-05-11 Compressor blade for gas turbine jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB21758/66A GB1119617A (en) 1966-05-17 1966-05-17 Compressor blade for a gas turbine engine

Publications (1)

Publication Number Publication Date
GB1119617A true GB1119617A (en) 1968-07-10

Family

ID=10168297

Family Applications (1)

Application Number Title Priority Date Filing Date
GB21758/66A Expired GB1119617A (en) 1966-05-17 1966-05-17 Compressor blade for a gas turbine engine

Country Status (3)

Country Link
US (1) US3524712A (en)
DE (1) DE1628365A1 (en)
GB (1) GB1119617A (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4969326A (en) * 1988-08-15 1990-11-13 General Electric Company Hoop shroud for the low pressure stage of a compressor
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine
DE10014189A1 (en) * 2000-03-23 2001-09-27 Alstom Power Nv Blade fastening for rotating machinery has blades fitted in slots without play or with pretensioning so that torsional moments acting on inner platform or blade roots oppose torsional moments acting upon outer platform or support wing
US7934907B2 (en) * 2004-07-21 2011-05-03 Delta T Corporation Cuffed fan blade modifications
US7252478B2 (en) * 2004-07-21 2007-08-07 Delta T Corporation Fan blade modifications
US7578655B1 (en) * 2006-05-20 2009-08-25 Florida Turbine Technologies, Inc. Composite gas turbine fan blade
AU2008276406B2 (en) * 2007-03-01 2012-03-08 Delta T, Llc Angled airfoil extension for fan blade
EP2093378A1 (en) * 2008-02-25 2009-08-26 ALSTOM Technology Ltd Upgrading method for a blade by retrofitting a winglet, and correspondingly upgraded blade
US8944774B2 (en) * 2012-01-03 2015-02-03 General Electric Company Gas turbine nozzle with a flow fence
US8842000B2 (en) 2012-07-17 2014-09-23 4Front Engineered Solutions, Inc. Fire control systems
US9874214B2 (en) 2014-01-28 2018-01-23 4Front Engineered Solutions, Inc. Fan with fan blade mounting structure
US9726192B2 (en) 2015-03-31 2017-08-08 Assa Abloy Entrance Systems Ab Fan blades and associated blade tips
US10060441B2 (en) * 2015-05-26 2018-08-28 Pratt & Whitney Canada Corp. Gas turbine stator with winglets
GB2545711B (en) * 2015-12-23 2018-06-06 Rolls Royce Plc Gas turbine engine vane splitter
FR3063663B1 (en) * 2017-03-13 2021-02-26 Mecachrome France PROCESS FOR MANUFACTURING COMPLEX SHAPED METAL ALLOY PARTS

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-blade lashing
US1998393A (en) * 1933-09-30 1935-04-16 Gen Electric Turbine bucket
CH238023A (en) * 1943-07-31 1945-06-15 Sulzer Ag Turbomachine blades and processes for their manufacture
US2463340A (en) * 1945-02-22 1949-03-01 Wiberg Oscar Anton Axial flow turbine blade structure
CH246346A (en) * 1945-06-14 1946-12-31 Escher Wyss Maschf Ag Method for fastening rotating blades by welding to the blade carrier of rotary machines.
FR949459A (en) * 1947-07-09 1949-08-31 Blades for rotors
GB680014A (en) * 1949-09-30 1952-10-01 Rolls Royce Improvements in or relating to blades for gas-turbine engines
US3216699A (en) * 1963-10-24 1965-11-09 Gen Electric Airfoil member assembly
US3394918A (en) * 1966-04-13 1968-07-30 Howmet Corp Bimetallic airfoils
US3396905A (en) * 1966-09-28 1968-08-13 Gen Motors Corp Ducted fan

Also Published As

Publication number Publication date
US3524712A (en) 1970-08-18
DE1628365A1 (en) 1971-07-08

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