GB1269172A - Blade for compressor and method of fabricating said blade - Google Patents

Blade for compressor and method of fabricating said blade

Info

Publication number
GB1269172A
GB1269172A GB44803/70A GB4480370A GB1269172A GB 1269172 A GB1269172 A GB 1269172A GB 44803/70 A GB44803/70 A GB 44803/70A GB 4480370 A GB4480370 A GB 4480370A GB 1269172 A GB1269172 A GB 1269172A
Authority
GB
United Kingdom
Prior art keywords
blade
die
fibres
plies
pressure
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
GB44803/70A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1269172A publication Critical patent/GB1269172A/en
Expired legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/16—Making alloys containing metallic or non-metallic fibres or filaments by thermal spraying of the metal, e.g. plasma spraying
    • 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
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • Organic Chemistry (AREA)
  • Composite Materials (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Abstract

1,269,172. Producing metal articles etc.; forging. UNITED AIRCRAFT CORP. 21 Sept., 1970 [6 Oct., 1969], No. 44803/70. Headinsg B3A and B3H. [Also in Division F1] A compressor blade is made by securing boron fibres 12 in parallel relationship to an aluminium alloy backing sheet 14, cutting the sheet into shaped plies 18 which vary in length and width, stacking the plies one above the other and then compacting the assembly in a mould to form the blade shape. The fibres 12 may have a tungsten core and be coated with silicon carbide, the fibres being secured to sheet 14 by a coating 16 of aluminium alloy applied by plasma spraying. The plies 18 are stacked on both sides of a central aluminium core 24, the smallest ply 20 being innermost and the largest 22 outermost, and are tack welded in position prior to moulding. In the latter operation the stacked plies 18 are placed between the two parts of a die 32 disposed between pressure plates 34, 36 slidable in a housing 38 heated by an induction coil 40. The die 32 is heated in a high vacuum to between about 549‹ and 566‹ C., i.e. about 25‹ C. below the melting point of the aluminium alloy and then a pressure of about 246 kg/cm.<SP>2</SP> is applied causing the alloy to flow and fill the voids between the fibres 12. Stops 44 limit the movement of the plates 34, 36 towards each other. The temperature and pressure are maintained for about 1¢ hours after which the die 32 and blade are allowed to cool while the pressure is maintained. The blade is removed from the die and any excess alloy 42 trimmed-off. If not added prior to moulding, a pair of profiled root elements (30, Figs. 8, 9, not shown) are then secured to the blade.
GB44803/70A 1969-10-06 1970-09-21 Blade for compressor and method of fabricating said blade Expired GB1269172A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US86402169A 1969-10-06 1969-10-06

Publications (1)

Publication Number Publication Date
GB1269172A true GB1269172A (en) 1972-04-06

Family

ID=25342343

Family Applications (1)

Application Number Title Priority Date Filing Date
GB44803/70A Expired GB1269172A (en) 1969-10-06 1970-09-21 Blade for compressor and method of fabricating said blade

Country Status (5)

Country Link
US (1) US3600103A (en)
JP (1) JPS4924923B1 (en)
DE (1) DE2047209A1 (en)
FR (1) FR2065431A5 (en)
GB (1) GB1269172A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2147055A (en) * 1983-09-23 1985-05-01 Gen Electric Hollow blade

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3699623A (en) * 1970-10-20 1972-10-24 United Aircraft Corp Method for fabricating corrosion resistant composites
US3886647A (en) * 1971-07-07 1975-06-03 Trw Inc Method of making erosion resistant articles
US3717419A (en) * 1971-07-09 1973-02-20 Susquehanna Corp Turbine blade
US3713752A (en) * 1971-10-28 1973-01-30 United Aircraft Corp Composite blade for a gas turbine engine
US3752600A (en) * 1971-12-09 1973-08-14 United Aircraft Corp Root pads for composite blades
US3903578A (en) * 1972-02-28 1975-09-09 United Aircraft Corp Composite fan blade and method of construction
US3799701A (en) * 1972-02-28 1974-03-26 United Aircraft Corp Composite fan blade and method of construction
US3749518A (en) * 1972-03-15 1973-07-31 United Aircraft Corp Composite blade root configuration
US3756745A (en) * 1972-03-15 1973-09-04 United Aircraft Corp Composite blade root configuration
FR2195255A5 (en) * 1972-08-04 1974-03-01 Snecma
US3942231A (en) * 1973-10-31 1976-03-09 Trw Inc. Contour formed metal matrix blade plies
US3981616A (en) * 1974-10-22 1976-09-21 The United States Of America As Represented By The Secretary Of The Air Force Hollow composite compressor blade
US4006999A (en) * 1975-07-17 1977-02-08 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Leading edge protection for composite blades
US4022547A (en) * 1975-10-02 1977-05-10 General Electric Company Composite blade employing biased layup
US4000956A (en) * 1975-12-22 1977-01-04 General Electric Company Impact resistant blade
US4043703A (en) * 1975-12-22 1977-08-23 General Electric Company Impact resistant composite article comprising laminated layers of collimated filaments in a matrix wherein layer-layer bond strength is greater than collimated filament-matrix bond strength
CA1042641A (en) * 1975-12-24 1978-11-21 Westinghouse Canada Limited Manufacture of composites for turbine blades
US4108572A (en) * 1976-12-23 1978-08-22 United Technologies Corporation Composite rotor blade
US4111606A (en) * 1976-12-27 1978-09-05 United Technologies Corporation Composite rotor blade
US4178667A (en) * 1978-03-06 1979-12-18 General Motors Corporation Method of controlling turbomachine blade flutter
US4301584A (en) * 1980-01-31 1981-11-24 United Technologies Corporation Method of forming fiber and metal matrix composite
US4583274A (en) * 1982-03-01 1986-04-22 Trw Inc. Method of making an airfoil
US4472866A (en) * 1982-03-01 1984-09-25 Trw Inc. Method of making an airfoil
US4856162A (en) * 1985-12-30 1989-08-15 United Technologies Corporation Fabrication of bonded structures
US4762268A (en) * 1986-05-02 1988-08-09 Airfoil Textron Inc. Fabrication method for long-length or large-sized dense filamentary monotapes
DE3710321C1 (en) * 1987-03-28 1988-06-01 Mtu Muenchen Gmbh Fan blade, especially for prop fan engines
US5141400A (en) * 1991-01-25 1992-08-25 General Electric Company Wide chord fan blade
US5375978A (en) * 1992-05-01 1994-12-27 General Electric Company Foreign object damage resistant composite blade and manufacture
US5449273A (en) * 1994-03-21 1995-09-12 United Technologies Corporation Composite airfoil leading edge protection
US5486096A (en) * 1994-06-30 1996-01-23 United Technologies Corporation Erosion resistant surface protection
JP3094320B2 (en) * 1994-11-02 2000-10-03 株式会社先進材料利用ガスジェネレータ研究所 Preform for FRM disc
US5876651A (en) * 1996-05-29 1999-03-02 United Technologies Corporation Method for forming a composite structure
FR2867095B1 (en) * 2004-03-03 2007-04-20 Snecma Moteurs METHOD FOR MANUFACTURING A HOLLOW DAWN FOR TURBOMACHINE
US7753653B2 (en) * 2007-01-12 2010-07-13 General Electric Company Composite inlet guide vane
US8123463B2 (en) * 2008-07-31 2012-02-28 General Electric Company Method and system for manufacturing a blade
US8794925B2 (en) 2010-08-24 2014-08-05 United Technologies Corporation Root region of a blade for a gas turbine engine
CN108087318A (en) * 2017-12-14 2018-05-29 中国航发沈阳发动机研究所 A kind of mixed structure composite material blade

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2621140A (en) * 1940-08-28 1952-12-09 Comp Generale Electricite Method for molding propeller blades
US2746514A (en) * 1950-04-06 1956-05-22 Cincinnati Testing And Res Lab Machine for making compressor blades
US2929755A (en) * 1958-07-24 1960-03-22 Orenda Engines Ltd Plastic blades for gas turbine engines
US3098723A (en) * 1960-01-18 1963-07-23 Rand Corp Novel structural composite material
US3248082A (en) * 1965-08-19 1966-04-26 Whitfield Lab Inc Reinforced gas-turbine blade or vane

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2147055A (en) * 1983-09-23 1985-05-01 Gen Electric Hollow blade

Also Published As

Publication number Publication date
US3600103A (en) 1971-08-17
JPS4924923B1 (en) 1974-06-26
DE2047209A1 (en) 1971-04-15
FR2065431A5 (en) 1971-07-23

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