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Aviation History
1969
1969 - 0035.PDF
Designed by the Small Engine Division of Rolls-Royce, the BS360 tur- boshaft engine will power the West/and WG./3 helicopter which is being developed for the Ang/o-French helicopter programme. It is due to run early this year ISHIKAWAJIMA-HARIMA HEAVY INDUSTRIES Tokyo, Japan JRIOO and 200 Military single-shaft lift jets. Being developed by IHI in co-operation with Japanese National Aerospace Laboratories under research programme sponsored by Japanese Science and Technology Bureau. Initial version was 3,1531b thrust JR100 of 3221b weight, followed by lighter, higher mass flow JR120 of 2291b weight. Version now under development is JR200 of higher effi ciency and 20:1 thrust/weight ratio design objective. (JR200) Five-stage compressor, annular combustor, single-stage turbine. Take-off 4,5851b; mass flow 821b/sec; pressure ratio 4:1; weight 2801b. XJ11 Military single-shaft turbojet. Successor to J3 turbojet and being developed for VTOL applications. J3-IHJ.-F Military free-turbine aft-fan turbofan. Uses J3-IHI-3 turbojet as gas generator to energise aft-fan. (J3-IHI-3) Eight-stage compressor, annular combustor, single-stage compressor-turbine, single-stage fan-turbine, single-stage aft-fan. Take-off 3,7501b; b.p.r. 1.55:1; mass flow (overall) 1231b/sec; pressure ratio 4.2 :1; length 104.3in; diameter 32.8in; weight 1,0801b. J3 Military single-shaft turbojet. First post-war Japanese de velopment of turbine aero engine. Replaced Rolls-Royce Orpheus in Fuji TIF trainer. Applications Fuji TIB, 1XJ3-IHI-3 (2,6451b). Fuji TIC, 1XJ3- IHI-7 (3,0851b). Kawasaki P2-J, 2XJ3-IHI-7C (3,0801b) booster units. (J3-IHI-7) Eight-stage compressor, annular oombustor, single-stage turbine. Take-off 3,0851b; mass flow 561b/sec; pressure ratio 4.5:1 : length 72.85in; diameter 28.35in; weight 7941b. ISOTOV USSR GTD-350 Military free-turbine turboshaft. Powers twin-engined Mil Mi-2 helicopter and is in production in both USSR and Poland. (GTD-350) Seven-stage axial plus single-stage (single-sided) cen trifugal compressor, two-can reverse-flow combustor, single-stage compressor-turbine, two-stage power-4urbine. Integral dorsal- mounted gearbox. Take-off 395 s.h.p.; mass flow 4.831b/sec; pres sure ratio 5.9:1; length 53.15in; width 20.47in; height 24.80in: weight 2981b. TB-2-117 Military free-turbine turboshaft. Two of these engines, each rated at 1,500 s.h.p., power Mil Mi-8 helicopter. IVCHENKO USSR AI-25 Civil & military twin-spool turbofan. Smallest turbofan to enter airline service, the AI-25 powers the three-engined Yakovlev Yak-40. Also licence-built in Czechoslovakia by Motorolet to power the Aero L-39 trainer. (AI-25) Three-stage fan/l-p compressor, eight-stage h-p compres sor, annular combustor, single-stage h-p turbine, two-stage 1-p turbine. Take-off 3,3001b; b.p.r. 2:1; pressure ratio 9:1; length 76in; width 32in; height 35in; weight 7601b. AI-24 Civil single-shaft turboprop. One of most recent turboprops to be developed by USSR, the AI-24 powers the twin-engined Antonov An-24. Engine is flat-rated and operates at constant r.p.m. Applications Antonov An-24V Series 1, 2 X AI-24 (2,515 e,h.p.). Antonov An-24V Series II, An-24RV and An-24TV, 2XAI-24T (2,780 e.h.p.). (AI-24T) Ten-stage compressor, annular combustor, three-stage turbine. Forward-mounted integral gearbox. Take-off 2,820 eJi.p. with water injection; length 95.87in; weight 1,1001b. FLIGHT International. 2 January 1969 23 AI-20 Civil and military single-shaft turboprop. First known turbine engine from Ivchenko design bureau, and believed to be derived from Kuznetsov NK-4 turboprop. Applications Antonov An-lOA, 2XAI-20K (4,000 e.h.p.). Antonov An-12, 2XAI-20K (4,000 e.h.p.). Beriev Be-12, 2XAI-20D (4,015 e.h.p.). Ilyushin I1-18D and I1-18E, 2XAI-20M (4,250 e.h.p.). Ilyu- shin I1-18V, 2XAI-20K (4,000 e.h.p.). (AI-20M) Ten-stage compressor, cannular combustor with ten flame tubes, three-stage turbine. Forward-mounted integral gearbox. Take-off 4,250 e.h.p.; weight 2,2901b. KUZNETSOV USSR NK-144 Civil twin-spool augmented turbofan. Derived from NK-8 subsonic turbofan and being developed for Tupolev Tu-144 SST. Has afterburner providing 35 per cent static boost. (NK-144) Three-stage fan, eleven-stage h-p compressor, annular combustor, single-stage h-p turbine, two-stage 1-p turbine, after burner, thrust-reverser and variable nozzle. Take-off 28,6601b basic, 38,5801b with afterburning; b.p.r. 1:1; pressure ration 12:1; length 205in; diameter 59in; weight 6,2831b. NK-12 Civil and military single-shaft turboprop. World's most powerful turboprop engine. Drives eight-bladed contra-rotating pro pellers. Applications Antonov An-22 4XNK-12MA (15,000 e.h.p.). Tupo lev Tu-20, 4XNK-12M (14,795 e.h.p.). Tupolev Tu-114, 4XNK- 12MV (15,000 e.h.p.). (NK-12MV) Fourteen-stage compressor, cannular combustor, five- stage turbine. Forward-mounted integral gearbox. Take-off 15,000 e.h.p.; mass flow 1371b/sec; length 236.2in ; diameter 45.3in: weight 5,0701b. NK-8 Civil twin-spool turbofan. Largest subsonic Russian turbo fan developed through several versions. Applications Ilyushin 11-62 (first series aircraft), 4xNK-8-4 (23,1501b). Tupolev Tu-154, 3XNK-8-2 (20,9501b). (NK-8-4) Three-stage fan 1-p compressor, light-stage h-p com pressor, annular combustor, single-stage h-p turbine, two-stage 1-p turbine. Take-off 23,1001b; b.p.r. approximately 2:1; length 201in; diameter 56.8in ; weight 4,8501b. LYCOMING (Lycoming Division, Avco Corporation), Stanford, Connecticut, USA T5S 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. Has growth potential to 6,000 sii.p. and is also available in turboprop and turbofan forms. Applications Bell Huey Tug (prototype), 1X T55-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. TSS Military free-turbine turboprop. Propeller driving version of T55 turboshaft with sole application in single-engined North American' YAT-28E. (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; pres sure ratio 6.4:1; length 62.2in; diameter 24.2in; weight 7951b. PLF1 Civil twin-spool turbofan. Private venture development using T55 gas generator as core engine. Intended for short-haul transports. Latest versions are 5,2201b PLF1C-1 and 6,7001b PLF1C-2 of 6:1 and 8.2:1 b.p.r. respectively: both are based on T55-L-11. (PLFC1-1) Single-stage fan, seven-stage axial plus single-stage (single-sided) centrifugal compressor, annular reverse-flow com bustor, two-stage compressor-, and fan-, turbines. Take-off 5,2201b; b.p.r. 6:1; mass flow (overall) 2011b/sec; length 66.2in; diameter 41in; weight 1,0101b. T53 Military free-turbine turboshaft. Major turboshaft engine in operation with US Army. Has extensive application in Bell UH-1 Iroquois in widespread use in Vietnam war. Latest version is T53-L-15 of 1,160 s.h.p. Manufacture licensed to Piaggio, Klockner- Humboldt-Deutz and Kawasaki. Applications Bell Iroquois UH-1B, -1C, -ID and -IE, 1XT53-L-11 (1,100 s.h.p.). Bell UH-1H, UH-1L and TH-1L, 1XT53-L-13 (1,400 s.h.p.). Bell AH-1G Hueycobra, 1XT53-L-13 (1,400 s.h.p.). Canadair
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