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Aviation History
1974
1974 - 0051.PDF
FLIGHT International, 10 January 1974 TURBINE ENGINES OF THE WORLD T700-GE-700 Five-stage axial-plus-single-stage centrifugal com pressor with integral particle separator, annular combustor, two-stage compressor and power turbines. Military rating 1,500 s.h.p.; length 47in; width 25in; height 23in. TF34 Two-shaft turbofan. As the US Navy-financed engine for the Lockheed S-3A Viking, the TF34-GE-2 started scries production in September 1972, and the first of the present order for 101 S-3As should enter service in April this year. An ultimate total of 191 aircraft for the Navy is expected. A year ago the TF34-powered Fairchild Industries A-10A won the USAF's AX close-air-support competition and an initial batch of development aircraft is under construction. While the potential USAF requirement is for 600 A-lOAs, thus making the aircraft trebly important for the TF34 compared with the S-3A, there is to be a fly-off competition between the A-10A and the LTV A-7D Corsair II in March to determine which of the two is best to fulfil the close-air-support role. Total test time in the TF34 is in the region of 25,000hr, in cluding some 4,000 flight hours. The modified TF34-GE-100 ver sion for the A-10A is to be qualified late this year. Applications and projects Fairchild Industries A-10A <2X 9,0001b TF34-GE-100); Lockheed S-3A Viking (2X9,2751b TF34- GE-2); Rockwell International OV-10 Multi-Purpose Aircraft (2XTF34). TF34-GE-2 Single-stage fan, fourteen-stage h-p compressor, annular combustor, two-stage h-p turbine, four-stage 1-p tur bine. Take-off 9,2751b; bypass ratio 6-2:1; pressure ratio 21:1; mass flow 3381b/sec; length lOOin; diameter 52-3in; weight 1,1421b. TF37 (CF700) Two-shaft aft-fan turbofan. Military version of the CF700, the 4,2001b TF37-GE-1 powers the Bell Lunar Landing Research and Training Vehicles. TF39 Two-shaft turbofan. Sole application of this engine is the Lockheed C-5A Galaxy (4X41,1001b TF39-GE-I) for the USAF, of which about 80 have been built. Studies are under way on the use of two coupled C-5As as a ferry vehicle for the forthcoming space shuttle. The TF39 provided the basis for the CF6-6 civil tuvbofan. TF39-GE-1 One-and-a-half-stage fan, 16-stage h-p compressor, annular combustor, two-stage h-p turbine, five-stage 1-p tur bine. Take-off 41,1001b; bypass ratio 8:1; pressure ratio 26:1; mass flow l,5491b/sec; length 20-3in; diameter lOOin; weight 7,0261b. "Variable Cycle Engine Three-shaft turbofan. GE, together with P&W, is under-taking design studies of variable-cycle engines to meet a possible propulsion requirement for any future American SST. The GE design has fans on both the 1-p and i-p shafts, each with its own annular bypass duct and exhaust nozzle. The airflow is split downstream of each fan, with the second split feeding air to the core engine forming the h-p spool. The second fan bypass How embodies duct burning, and together with the core engine exhaust, is fitted with a noise suppressor. The variable configuration of the engine is aimed at achieving low noise at take-off with efficiency at supersonic cruise. GLUSHENKOV (USSR) Only two engines are known to have been produced by this design bureau—the 950 s.h.p. TVD-I0 free-turbine turboprop powering the twin-engined Beriev Be-30 transport, and the 900 s.h.p. GTD-3 turboshaft chosen for the twin-engined Kamov Ka-25 helicopter. Problems with the TVD-10 are reported to be the reason for termination of the Be-30 development pro gramme last year. HAMILTON STANDARD (USA) Hamilton Standard Division, United Aircraft Corporation. Headquarters: Windsor Locks, Connecticut 06096. Tel: (203) 623 1621. The Division engages in manufacture of a wide variety of aircraft, space and ground systems and equipment, including engine controls and starters, propellers and turbomachinery. For corporate details, see Pratt & Whitney Aircraft, page 50. QFT55 Geared variable-pitch turbofan. Under a unique com pany sponsored project, Hamilton Standard has built and tested an 8,3001b quiet turbofan demonstrator comprising an Avco Lycoming T55-L-11A core engine and Hamilton Standard Q-Fan variable-pitch fan with integral reduction gearing. The Q-Fan is a 13-blade single-stage unit of 54in diameter and carries the reduction gearing within its nose fairing, ahead of the fan to facilitate accessibility. Testing of the QFT55 to demonstrate fan-noise characteristics and fan/engine com patibility is Nasa-financcd and had reached iOOhr by mid- 1973. Other Nasa-backed Q-Fan work by Hamilton Standard has included construction of 20in and Oft diameter v-p fans for testing by Nasa. HINDUSTAN AERONAUTICS (India) Hindustan Aeronautics Ltd. Headquarters: PO Box 5150, Bangalore-560001. National corporation engaged in aircraft, aero-engine, ancil lary systems and accessories manufacture. Company em ployees 37,000. J972/73 corporate sales up to Rs771 million, £41 -2 million. HAL is the sole aircraft and aero-engine manufacturer in India, with the latter of the two activities being the smaller. Two of the company's six divisions are in production with engines, the newer Koraput Division licence-building Tuman- ski R-11-F2-300 and R-1I-F2S-300 afterburning turbojets for HAL licence-built MiG-21FIs and MiG-21Ms respectively; and the older Bangalore division licence-building the Turbomeca Artouste MB turboshaft for HAL licence-built Aerospatiale Alouette III and SA.3I5 helicopters, and three Rolls-Royce (1971) licensed engines—the Orpheus 701 and 703 turbojets for HAL licence-built Gnat Mk Is and HAL HF-24 Marut Mk 1 and 1(T), the Viper 11 turbojet for HAL H.IT-16 Mk 1 Kirans, and the Dart Mk 531 turboprop for HAL licence-built HS.748s. 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 been working on an afterburning version of the Orpheus 703, the R-1700, with a design rating of 6,6001b: this engine is intended for the Marut MklR. Other afterburning engines under considera tion for higher-performance versions of the Marut and for a proposed advanced strike aircraft for the 1980s, include the Snecma Atar 9K50 and M53, Rolls-Rovce/Turborncca Adour, and Turbo-Union RB.199. INSTYTUT LOTNICTWA (Poland) Instytut Lotnictwa. Headquarters: Warsaw 21 Okecie, Al. Krakowska 110/114. Tel: Warsaw 460993. 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-I1 Iskra trainer. Some 700 of these aircraft have been built. ISHIKAWAJIMA HEAVY INDUSTRIES (Japan) Aircraft Engine Division; ilshikawajima-Harima Heavy In dustries Ltd. Divisional headquarters; 3-5-1, Muftodcu-sho, Tanashi-shi Tokyo 188. Tel: (0424) 62-2111. Public company engaged in general engineering, shipbuilding and aero engine manufacture. Corporate assets Yen 1,087,648 million, £1,662 million, and employees 44,600. Corporate sales in 1972 Yen 439,759 million, £672 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 capability. Current production activities include licence- manufacture of the GE J79-GE-17 turbojets for McDonncll- 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 com pany is manufacturing its own 2,6501b J3-IHI-3 and 3,0901b J3-IHI-7C turbojets for Fuji TIB intermediate trainers and as auxiliary boosters on P-2Js. For the T-2, R-R has supplied 12 Adours and 50 more are on order—eight of which will be 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 this year, IHI will also handle all main tenance and major overhaul work on the R-R RB.21I turbofans powering All Nippon Airways TriStars. Design and development work bv IHI includes the FJR710 turbofan, and the 3,1501b JR100, 4,6301b JR200 and 5,0261b JR220 series of experimental lift-jets.
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