GB1269172A - Blade for compressor and method of fabricating said blade - Google Patents
Blade for compressor and method of fabricating said bladeInfo
- 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
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.
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)
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)
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)
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 |
-
1969
- 1969-10-06 US US864021A patent/US3600103A/en not_active Expired - Lifetime
-
1970
- 1970-09-21 GB GB44803/70A patent/GB1269172A/en not_active Expired
- 1970-09-25 DE DE19702047209 patent/DE2047209A1/en active Pending
- 1970-10-06 FR FR7037020A patent/FR2065431A5/fr not_active Expired
- 1970-10-06 JP JP45087809A patent/JPS4924923B1/ja active Pending
Cited By (1)
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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