GB1332595A - Metallic multicomponent fabricated aerofoil - Google Patents

Metallic multicomponent fabricated aerofoil

Info

Publication number
GB1332595A
GB1332595A GB5161971A GB5161971A GB1332595A GB 1332595 A GB1332595 A GB 1332595A GB 5161971 A GB5161971 A GB 5161971A GB 5161971 A GB5161971 A GB 5161971A GB 1332595 A GB1332595 A GB 1332595A
Authority
GB
United Kingdom
Prior art keywords
aerofoil
leading edge
metallic
axis
cast
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
GB5161971A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1332595A publication Critical patent/GB1332595A/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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Abstract

1332595 Making aerofoil components; welding by pressure GENERAL ELECTRIC CO 5 Nov 1971 [13 Jan 1971] 51619/71 Headings B3A and B3R [Also in Division F1] An aerofoil component, e.g. a gas turbine blade, comprises a metallic body portion to which is secured a metallic leading edge portion having at least one metallic grain the crystal direction of low elastic modulus of which is oriented less than 20 degrees from the axis of the edge of the aerofoil. The crystal direction is selected from the group represented by Miller indices <001>, <100> and <010>. The body portion (10, Fig. 1, not shown) may be of wrought or cast randomly oriented polycrystalline nickel based superalloy containing C, Cr, Ti, B, Al, W, Mo, Co and Zr in specified proportions. The leading edge portion (12) may be machined from a monocrystal cast ingot of the same alloy such that the <100> direction is located substantially along the aerofoil axis. Alternatively the leading edge portion may be machined from a directionally solidified cast columnar ingot such that the elongated dimension of the grains is located along the aerofoil axis. The body and leading edge portions may be secured together by diffusion bonding, e.g. as described in Specifications 1,302,160 and 1,299,983, a longitudinally extending channel (14) being provided along the interfaces of the portions.
GB5161971A 1971-01-13 1971-11-05 Metallic multicomponent fabricated aerofoil Expired GB1332595A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10615071A 1971-01-13 1971-01-13

Publications (1)

Publication Number Publication Date
GB1332595A true GB1332595A (en) 1973-10-03

Family

ID=22309763

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5161971A Expired GB1332595A (en) 1971-01-13 1971-11-05 Metallic multicomponent fabricated aerofoil

Country Status (6)

Country Link
JP (1) JPS4714052A (en)
BE (1) BE777978A (en)
DE (1) DE2201098A1 (en)
FR (1) FR2122174A5 (en)
GB (1) GB1332595A (en)
IT (1) IT946481B (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2936481A1 (en) * 1978-09-16 1980-03-27 Rolls Royce SHOVEL FOR A GAS TURBINE ENGINE AND METHOD FOR THE PRODUCTION THEREOF
FR2515728A1 (en) * 1981-11-03 1983-05-06 Rolls Royce FUNGUS VALVE FOR AN INTERNAL COMBUSTION ENGINE
WO1991009209A1 (en) * 1989-12-11 1991-06-27 Allied-Signal Inc. Radial turbine rotor with improved saddle life
CN103586647A (en) * 2013-10-14 2014-02-19 西安航空动力股份有限公司 Forming method of aeroengine hollow guide vane

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4864706A (en) * 1987-08-12 1989-09-12 United Technologies Corporation Fabrication of dual alloy integrally bladed rotors

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2936481A1 (en) * 1978-09-16 1980-03-27 Rolls Royce SHOVEL FOR A GAS TURBINE ENGINE AND METHOD FOR THE PRODUCTION THEREOF
FR2515728A1 (en) * 1981-11-03 1983-05-06 Rolls Royce FUNGUS VALVE FOR AN INTERNAL COMBUSTION ENGINE
WO1991009209A1 (en) * 1989-12-11 1991-06-27 Allied-Signal Inc. Radial turbine rotor with improved saddle life
CN103586647A (en) * 2013-10-14 2014-02-19 西安航空动力股份有限公司 Forming method of aeroengine hollow guide vane
CN103586647B (en) * 2013-10-14 2015-12-02 西安航空动力股份有限公司 A kind of forming method of aeroengine hollow guide vane

Also Published As

Publication number Publication date
DE2201098A1 (en) 1972-07-27
JPS4714052A (en) 1972-08-03
BE777978A (en) 1972-07-13
FR2122174A5 (en) 1972-08-25
IT946481B (en) 1973-05-21

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee