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Aviation History
1970
1970 - 0036.PDF
AERO ENGINES 1970 . . . version is 2,529 e.h.p. T55-L-9 based on T55-L-7 turboshaft and with North American Rockwell YAT-28E as sole application. Later version is 3,690 s.h.p. LTC4R-1 based on T55-L-11 and incorporat ing Lycoming "split-power" reduction gear. (T55-L-9) Seven-stage axial plus single-stage (single-sided) centri fugal compressor, annular reverse-flow combustor, single-stage compressor-turbine, two-stage power turbine. Front-mounted in tegral gearbox. Take-off 2,529 e.h.p.; mass flow 21.51b/sec; pressure ratio 6.4:1; length 62.2in; diameter 24,2in; weight 7951b. TS3 Military free-turbine turboprop. Propeller driving version of T53 turboshaft with company series designation of LTC1. Projected growth versions include LTClV-1 of 1,800 s.h.p. Applications Federal Aircraft Industries C. 3605, 1XT53-L-7A (1,150 e.h.p.). Grumman OV-1A and -IB Mohawk, 2xT53-L-7 (1,150 e.h.p.), Grumman OV-1C and -ID Mohawk, 2xT53-L-15 (1,203 e.h.p,). (T53-L-15) Similar configuration to T53-L-13 turboshaft but with front-mounted integral gearbox. Take-off 1,203 e.h.p.; mass flow 12.41b/sec; pressure ratio 7.4:1; length 58.4in; diameter 23in; weight 6051b. PLT-27 Civil and military free-turbine turboshaft. Private-venture Lycoming-funded development of new small 1,950 s.h.p. turboshaft of advanced, compact design as competitor to US Army-funded US General Electric GE12 and Pratt & Whitney ST9 turboshafts. Development proceeded throughout 1969. Engine weight is 2801b, length 37in and s.f.c. only 0.431b/s.h.p./hr. LTC4V Military free-turbine turboshaft. Projected advanced technology derivative of T55 turboshaft. Two versions are proposed the 5,000 s.h.p. LTC4V-1 and the 6,000 s.h.p. LTC4V-2. Potential applications include the Canadair CL-84-1C, VFW VC-500C2 and Sikorsky S-65-300. T55 Military free-turbine turboshaft. Based on earlier T53 turbo shaft and developed under joint US Army/USAF support. Has major application in Boeing Vertol Chinook helicopter being exten sively operated in Vietnam. Company series designation is LTC4, with 4,340 s.h.p. LTC4B-12 as projected growth version. Applications Bell Huey Tug (prototype), 1 XT55-L-7B (2,650 s.h.p.). Bell Huey Tug (production), 1XT55-L-7C (2,850 s.h.p.). Boeing Vertol CH-47A Chinook, 2XT55-L-7 (2,650 s.h.p.). Boeing Vertol CH-47B Chinook, 2XT55-L-7C (2,850 s.h.p.). Boeing Vertol CH- 47C Chinook 2XT55-L-11 (3,750 s.h.p.). Boeing Vertol Model 297 project, 3XT55-L-11 (3,750 e.h.p.). (T55-L-11) Seven-stage axial plus single-stage (single-sided) cen trifugal compressor, annular reverse-flow combustor, two-stage com pressor- and power-turbines. Direct drive at front. Take-off 3,750 s.h.p.; mass flow 27.41b/sec; pressure ratio 6.0:1; length 44in; diameter 24.2in ; weight 6701b. T53 Military free-turbine turboshaft. Major turboshaft in opera tion with US Army, especially in Vietnam. Has extensive application in Bell UH-1 Iroquois family of helicopters. Company series desig nation is LTC1. Current production version is 1,400 s.h.p. T53-L-13 which is also being licence-manufactured by Piaggio, Kawasaki and Klockner-Humboldt-Deutz. Projected growth version is 1,800 s.h.p. LTC1S-1. Ten thousandth T53 delivered early in 1969. Applications Agusta A.123, 2XT53 (1,800 s.h.p.). Bell Iroquois UH-1B, -ID and -IE, 1XT53-L-11 (1,100 s.h.p.). Bell UH-1C, -1H and -1L, HH-1K and TH-1L, lxT53-L-13 (1,400 s.h.p.). Bell Huey Cobra AH-1G and -1J, 1XT53-L-13 (1,400 s.h.p.). Bell YH-40, 1XT53-L-13 (1,400 s.h.p.). Canadair CL-84, 2XLTC1K-4A (1,400 s.h.p.). Canadair CL-84-1, 2XLTCK1K-4C (1,500 s.h.p.). Kaman HH-43B Huskie, 1XT53-L-11 (1,100 sih.p.). Kaman HH-43F Huskie, 1XT53-L-13 (1,400 s.h.p.). (T53-L-13) Five-stage axial plus single-stage (single-sided) centri fugal compressor, annular reverse-flow combustor, two-stage com pressor-turbine, two-stage power-turbine. Take-off 1,400 s.h.p.; mass flow 12.81b/sec; pressure ratio 7.4:1; length 47.6in; diameter 23.0in; weight 5491b. T53 Civil free-turbine turboshaft. Counterpart commercial series to T53 military turboshaft. Proposed growth version is 1,800 s.h.p. T5319A. Applications Bell 204B, 1XT5311A (1,100 s.h.p.). Bell 205A, 1XT5313A (1,400 s.h.p.). (T5313A) Similar configuration, rating and dimensions as T53-L-13. MAN MAN Turbo GmbH (subsidiary of MAN AG). Headquarters: Miinchen-Allach, West Germany. The aero engine development activities of MAN Turbo, together with those of Daimler-Benz, were transferred in the autumn of 1968 to a new joint company, Entwicklungsgesellschaft fur Turbomotoren mbH. Subsequently the responsibilities of T-E were taken over by a further new joint company, Motoren und Turbinen Union Munich rtHSTrnnrerflononai, t January t GmbH. The former products of MAN Turbo are listed under MTU. MICROTURBO Microturbo SA (subsidiary of Ateliers Semca). Headquarters: Toulouse, Haute Garonne, France. Cougar Military single-shaft turbojet, A new ultra-small turbojet for target drones, rated at 1321b. Weight 58.41b. Eclair Civil and military single-shaft turbojet. Based on Micro- turbo APU technology, is an ultra-small turbojet for use in sail planes and drones. Applications Caproni Vizzola Calif A-21J, lx Eclair (1761b). Fauvel Aile Volante AV45, lxEclair (1761b). Fauvel AV46 and AV48, 1 x Eclair (1761b). (Eclair Type 012-01) Single-stage (single-sided) centrifugal com pressor, annular reverse-flow combustor, single-stage turbine. Take-off 1761b; length 23.9in; width 19.9in; height 12.7in; weight approx 771b. MIKULIN (USSR) AM-3M Civil single-shaft turbojet. Developed from early Mikulin M-209 military turbojet. Is the most powerful turbojet in com mercial operation. , Applications Tupolev Tu-104A, 2XAM-3M (19,1801b). Tupolev Tu-104B, 2XAM-3M-500 (21,3851b). (AM-3M-500) Eight-stage compressor, cannular combustor with 14 flame tubes, two-stage turbine. Take-off 21,3851b; mass flow 3201b/sec; pressure ratio 6.4:1; length 210.03in; diameter 55.12in; weight 5,0701b. MITI Ministry of International Trade and Industry, Tokyo, Japan. Turbofan Project Civil two-shaft turbofan. The MITI plans to fund a 15 billion yen programme for development of a family of advanced technology high b.p.r. turbofans of 10,0001b and 20,0001b. Japanese industry is to participate in the programme and Ishika- wajima-Harima Heavy Industries has already initiated component studies and is testing high b.p.r. fans, (Stage One turbofan) Take-off 10,0001b; b.p.r. 7.5:1; pressure ratio 22:1; weight approx 1,7501b. (Stage Two turbofan) Take-off 20,0001b; b.p.r. 8:1; pressure ratio 25:1; weight 3,3401b. MITSUBISHI Mitsubishi Heavy Industries Ltd. Engine Works: Nagoya City, Japan The company's Engine Works is engaged in licenced-manufaeture of 317 s.h.p. Allison T63-A-5A turboshafts for Kawasaki-built Hughes Model 369HM (500M) single-ehgined helicopters, some 400 to 500 of which are being supplied to the Japanese Ground Self- Defence Force. jk MTU Mo'oren und Turbinen Union Munchen GmbH (joint company of MAN AG and Daimler-Benz AG). Headquarters: Munich, West Germany. MTU was formed in July 1969 to combine the total aero engine activities of MAN Turbo GmbH (MAN AG subsidiary) and Daimler-Benz AG. As a consequence it took over the aero-engine development responsibilities of the previous joint company, Entwick lungsgesellschaft ftir Turbomotoren mbH. (A sister company Motoren und Turbinen Union Friedrichshafen GmbH was also formed in July 1969 to combine certain diesel engine activities of the two parent companies.) In addition to the engines listed below, MTU Munchen is licence-manufacturing 470 6,100 e.h.p. Rolls- Royce Tyne RTy.22 turboprops for the Transall C.160 transport as part of the European consortium (MTU, Snecma, Fabrique Nationale and R-R) producing Tynes for the C.160 and Breguet Atlantic. MTU is also licence-manufacturing an improved version of the US General Electric J79-GE-11 turbojet designated J79- MAN-J1K, for European-built Lockheed F-104G fighters. Other manufacturing licences held by MTU are for the US General Electric T64 turboshaft/turboprop and United Aircraft of Canada FT6A-27 turboprop. RB.199 Military three-shaft augmented turbofan. This is a jointly funded engine by West Germany, Britain and Italy for powering the Panavia MRCA-75 aircraft. The RB.199 prgoramme is the responsi bility of a new joint company Turbo-Union Ltd (q.v.), with Rolls-Royce having engine design and development leadership. RB.193 Military two-shaft vectored thrust turbofan. Rated at 10,0001b, is being developed as a joint project by MTU and Rolls- Royce under a £8 million contract from the West German Ministry of Defence. Sole application is VFW-Fokker VAK 191B systems, ( test aircraft for the MRCA-75. First ran at R-R Derby in December 1967. Flight engines were scheduled to have been delivered November 1969 with seven RB.193s being available for the VAK 191B flight test programme planned to start in February 1970.
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