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Aviation History
1975
1975 - 0032.PDF
14 Directory TURBINE ENGINES OF THE WORLD 21M fighters, which are being built by HAL through to 1980. The older Bangalore Division-builds the Turbomeca Artouste IIIB turboshaft for HAL-built Aerospatiale Alouette III and SA.315 helicopters, and there are three Rolls- Royce licensed engines—the Orpheus 701 and 703 turbojets for HAL licence-built Gnat Mk Is and HAL HF-24 Marut Mk I and I(T)s, the Viper II turbojet for HAL HJT-16 Mk I Kirans, and the Dart Mk 531 turboprop for HAL licence-built HS.748s (production of which has been temporarily suspended). The Bangalore Division has also been developing its 2,5001b HJE- 2500 turbojet (for the Kiran) over a period of years, and India's Gas Turbine Research Establishment has developed an after burning version of the Orpheus 703, the R.I700, with a design rating of 6,6001b; this is intended for the Marut Mk IR. The Gnat Mk 2 (officially named the Ajeet) which is to fly in June this year and enter production in 1976—77, is powered by a higher-rated Orpheus 701 of 4,6701b. In addition HAL has two "significant engine projects" in hand which are to be tested this year. These are probably connected with India's projected deep- penetration fighter-bomber, and with upgrading the performance of existing service aircraft. Present company objectives are aimed at a general expansion of its design and development abilities—and at increasing HAL's overseas earnings both by exporting existing types of aircraft (and their engines) and by attracting subassembly and com ponent work. INSTYTUT LOTNICTWA (Poland) Instytut Lotnictwa. Headquarters: Warsaw 21 Okecie, Al. Krakowska 110/114: Tel: Warsaw 480993. National aviation institute engaged in general aerospace R&D including aircraft turbine development. IL's only known aero engines are the SO-1 and SO-3 axial turbojets rated at 2,2051b and powering earlier and later ver sions respectively of the WSK-Mielec TS-11 Iskra trainer. Some 700 of these aircraft have been built. ISHIKAWAJIMA-HARIMA HEAVY INDUSTRIES (Japan) Aircraft Engine Division, Ishikawajima-Harima Heavy Industries Ltd. Divisional headquarters: 3-5-1, Mukodai-sho, Tanashi-shi, Tokyo 188. Tel: (0424) 62-2111. Public company engaged in general engineering, shipbuilding and aero-engine manufacture. Corporate assets Yl,293,563 million, £1,856 million, and employees 44,600. Corporate sales in 1973 up to Y580,044 million, £831-6 million, of which aero engine sales accounted for some 3 per cent. IHI is Japan's leading manufacturer of aero-engines, and is the only company there with a design and development capa bility. Current production activities include licence manufacture of the GE J79-GE-17 turbojets for McDonnell Douglas/Mitsubishi F-4EJ fighters, GE T64-GE-10 turboprops for Lockheed/ Kawasaki P-2J patrol aircraft and Shin Meiwa PS-l/RS-1 flying boats, GE CT58-110s and -180 turboshafts for Sikorsky/ Mitsubishi HSS-2/2As and Boeing Vertol/Kawasaki V-107-II/ IIAs, and Rolls-Royce/Turbomeca Adour Mk 801X turbofans for the Mitsubishi T-2 trainer. In addition, the company is manu facturing its own 2,6501b J3-IHI-3 and 3,0901b J3-IHI-7C turbojets for Fuji T-1B intermediate trainers and as auxiliary boosters on P-2Js. For the T-2, R-R supplied 12 Adours and 50 more are on order—eight of-which have been assembled in the UK and the remainder in Japan, with IHI manufacturing some of the components. There are plans to build up to 127 T-2s by 1976, beyond when R-R sees a likely Japanese requirement for more than 600 Adours. The Fuji XT-3 trainer project is a further possible application for the Adour. From April last year, IHI has been handling all maintenance and major overhaul work on the R-R RB.211 turbofans powering All Nippon Airways Tristars. Design and development work by IHI includes the FJR710 turbofan, and the 3,1501b JR100, 4,6301b JR200 and 5,0261b JR220 series of experimental lift-jets. FLIGHT International. 2 January 1975 FJR710 Two-shaft turbofan. Testing started in May 1973 of this first wholly-Japanese-designed commercial transport engine. Nine 11,0001b FJR710/10s were scheduled to have been built by the middle of last year and testing is to continue through this year to complete the first five-year stage of the programme, costing about Y6,700 million, £9-6 million. This included con struction and test of the FJR710/10, and a feasibility study of a larger 22,0001b-33,0001b FJR710/20. During the second four- year stage (1976-1979) of the programme, to be financed by the Government at Y17,000 million, £24-4 million, this engine will be developed to series production standard, including flight qualification. No application, however, is envisaged at present. Financial support for the two-stage programme is to be supplied via the Ministry of International Trade and Industry, with IHI and the National Aerospace Laboratory heading an industry design and development group which' also includes Mitsubishi and Kawasaki. FJR710 Single-stage fan and single-stage i-p compressor, twelve-stage h-p compressor, annular combustor, two-stage h-p turbine, four-stage 1-p turbine. Take-off 11,0001b; bypass ratio 6-5:1; pressure ratio 20:1; diameter 47in; weight 2,7501b. ISOTOV (USSR) This bureau has produced only two engines, both free-turbine two-shaft turboshafts. They are the small GTD-350 for the Mil Mi-2 helicopter and the TV2-117A powering the Mil Mi-8 and Mil 24 helicopters. The GTD-350 is also licence-built by PZL in Poland for Polish-built Mi-2s. A third engine, the 810 s.h.p. TVD-850 turboprop powering the Antonov An-28, has also recently been attributed to Isotov. GTD-350 Seven-stage axial plus single-stage centrifugal com pressor, annular reverse-flow combustor, single-stage compressor turbine, two-stage power turbine. Integral dorsal-mounted gearbox. Take-off 400 s.h.p.; pressure ratio 6-0:1; mass flow 4-81b/sec; length 53-lin; width 20-9in; height 26-8in; weight 2971b. TV2-117A Ten-stage compressor, annular combustor, two- stage compressor and power turbines. Direct drive. Take-off 1,500 s.h.p.; pressure ratio 6-6:1; mass flow 17-81b/sec; length 94-0in; width 21-5in; height 29-25in; weight 7271b. IVCHENKO (USSR) This bureau has specialised in engines at the lower performance end of the scale, including the AI-8 and AI-9 APUs, the AI-20 and AI-24 turboprops, and the AI-25 turbofan. AI-20 Single-shaft turboprop. This engine powers the Antonov An-lOA (4 X 4,000 e.h.p. AI-20K); Antonov An-12 (4 X 4,250 e.h.p. AI-20M);BerievBe-12 (2 x 4,000 e.h.p. AI-20D); Ilyushin I1-18B (4 X 4,000 e.h.p. AI-20K); Ilyushin I1-18D and 18E (4 x 4,250 e.h.p. 4,250 s.h.p.). AI-20M Ten-stage compressor, annular combustor, three-stage turbine. Integral front-located gearbox. Take-off 4,250 e.h.p.; pressure ratio 7-6:1; mass flow 45-61b/sec; length 121-8in; width 33-15in; height 46-5in; weight 2,2921b. AI-24 Single-shaft turboprop. Virtually a smaller version of the AI-20, this engine also powers a series of Antonov transport aircraft including the An-24T, -24RT, -24V-2 and -24RV (2 X 2,550 e.h.p. AI-24A) and the later-series An-24T (2 X 2,800 e.h.p. AI-24T). AI-24T Ten-stage compressor, annular combustor, three-stage turbine. Integral.front-located gearbox. Take-off 2,800 e.h.p.; pressure ratio 7-05:1; mass flow 31-71b/sec; length 92-4in; width 26-7in; height 42-3in; weight 1,3231b. AI-25 Two-shaft turbofan. Probably Russia's best known aviation powerpla.nt, the AI-25 powers the Yak-40 trijet and is licence-manufactured in Czechoslovakia as the Motorlet/Walter Titan, This turbofan is also to power the novel single-engined WSK-Mielec M-15 crop-spraying aircraft, first flight of which is now imminent. Aeroflot is reported to have placed orders for some 3,000 of this new Polish/Russian aircraft. Basic rating of the AI-25 is 3,3001b, but a later version powering the Yak-40B for the Soviet Air Force has turbine cooling and is rated at
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