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Aviation History
1974
1974 - 0064.PDF
60 TURBINE ENGINES OF THE WORLD PT6T Twin Pac (T400 and T402) Coupled free-turbine two- shaft turboshaft. Comprising coupled PT6B turboshafts with an integral front-located gearbox, the Twin Pac is in pro duction as the 1,800 s.h.p. commercial PT6T-3 and military T400-CP-400. The engine has been certificated with a water- injection system capable of increasing power by ten per cent, for use in high ambient temperatures. Some 540 Twin Pacs had been delivered by the beginning of 1973. Early this year the uprated 1,970 s.h.p. PT6T-6/T402 will be military- qualified following an extensive test programme, and deliveries of the T402 will start shortly; the engine is in tended to provide such applications as the Bell AH-1J and UH-1N with improved payload and performance. Two high lights of 1973 were an Iranian order for 202 AH-Us, and a Chinese order for PT6T-3s for a projected twin-turbine helicopter. Applications and projects. Agusta Bell AB 212 (1X1,800 s.h.p. PT6T-3); Bell 212 Twin (1X1,800 s.h.p. PT6T-3); Bell UH-1N (1X1,800 s.h.p. T400-CP-400); Bell AH-1J (1X1,800 s.h.p. T400-CP-400); Sikorsky H-34 (1X1,800 s.h.p. PT6T-3); Sikorsky S-58T (1X1,800 s.h.p. PT6T-3); Sikorskv S-69 XH-59A (1X1,800 s.h.p. PT6T-3). UNITED AIRCRAFT OF WEST VIRGINIA (USA) United Aircraft of West Virginia Incorporated. Headquarters: Benedum Airport, Bridgeport, West Virginia. Tel: (304) 842 5421. Subsidiary of United Aircraft of Canada Ltd engaged in aircraft gas turbine assembly and test. This company assembles and tests T400-CP-400 turboshafts for installation in military helicopters ordered by the US armed services. The engine parts are supplied by UACL. WILLIAMS RESEARCH (USA) Williams Research Corporation. Headquarters: 2280 West Maple Road, Walled Lake, Michigan 48088. Tel: (313) 624-5200. Private company engaged in aero- and non-aero gas-turbine manufacture. Corporate sales in the multi-million dollar bracket. The bar charts on this and the next page convey the following information: (1) the range of engines surveyed, i.e. turbofan, turbojet, turboprop or turboshaft; (2) the civil (C) or military (M) origin of a design; (3) the status of an engine programme (project, development and production; in one case, that of the RB.211, the diagonal line indicates a project of lower power than the original engine); (4) the basic take-off rating of an engine series, with the afterburning thrust, where applicable, denoted by a thick vertical line; and (5) the range of engines on the market in a given performance bracket. The relative timescales of programmes is indicated by the amount of "white" showing on the bars, so it is possible to see at a glance how well a particular bracket is stocked with current or next-generation engines. Project or design study Demonstrator or development Production and /or service TURBOFAMS Fig 1 0-2,500lb, 0-11kN r 106 : ' , .'; - : F107 JWR1i Na .. pro] Au JT15D ' ,1 ri '•'y-\U "/A u "'•'\u • ••--":.; !M .. : ." -*:i_r"" .. 1' |c c 0 500 1,000 1,500 2,000 2,500 FLIGHT International, 10 January 1974 This company has specialised in the development of ultra- small gas-turbines for aero, automotive, industrial and marine duties. In addition to propulsion turbines, the com pany manufactures APUs. A total of about 2,000 engines have been built to date. F107 (WR19) Two-shaft turbofan. Originated by Williams Besearch for the Bell Aerosystems Flying Belt, this turbofan in its uprated WR19-2 version was one of two competing engines to power the USAF's AGM-83 Scad (Subsonic Cruise Armed Decoy) which was cancelled last year. In this installa tion the engine was designated F107-WR-100 and was rated at 6251b, The F107 is currently being considered for use in a future US Navy cruise missile. The WR19 has also been experimentally installed in the Kaman Saver (Stowable Air crew Vehicle Rotoseat) and is probably also the power unit for Williams Research's WASP (Williams Aerial Systems Platform) which entered flight-test at the end of 1972 under US Navy contract. WR19 Two-stage fan and two-stage i-p compressor, single- stage h-p compressor, annular combustor, single-stage h-p turbine, two-stage 1-p turbine, Take-off 4301b; bypass ratio 1:1; pressure ratio 12:1; mass flow approximately 4'41b/ sec; length 24in; diameter 12in; weight 671b. J400 (WR24) Single-shaft turbojet. Currently Williams Re search's main aero product, the WR 24 series are derived from the earlier WR2-6 turbojet: Applications and projects. Northrop JVIQM-74C Chukar (IX 1211b WR24-0/YJ400-WR-400); Northrop MQM-74C Chukar2 (1 X 1701b WR24-7/J400-WR-401); Northrop VSTT (Variable Speed Training Target) (IX2001b WR24-17). WR24-6 Single stage compressor, annular combustor, single- stage turbine. Take-off 1211b; pressure ratio 4-2:1; mass flow 2-21b/sec; length I9in; diameter llin; weight 301b. Stagg Single-shaft gas-generator. Williams Research is one four contractors participating in the US Army's Stagg (Small Turbine Advanced Gas Generator) programme. Mass flow is less than lOlb/sec. WR2 Single-shaft turbojet. First quantity-produced Williams Research engine, the 1251b-thrust WR2-6 powers the Canadair CL-89 AN/USD-501 reconnaissance drone. WR2-66 Single-stage compressor, annular combustor, single- stage turbine. Take-off 1251b, pressure ratio 4:1; mass flow 2-21b/sec; length 22-8in; diameter 10-8in; Weight 301b. Fig2 2,500lb-5,000lb, 11kN-22kN ALF301 Model 490 & Lyrza Tic? n ; Al 25 & 1 n i CF700&TF Model 440 '<'' F104& ATF 3••' JT25D ,/,,/" •'•] Jc i ' ' M ! " •• , -, • ,, "" I ' He JC& M \ H MM ' < ; 1 . -, ;c& M ,1 0 1,000 2,000 3,000 4,000 5,000 Fig3 5,000lb- 10,0001b, 22kN-44-5kN M45M (RB.407) %.(»•! 1 Viper RB.401 F102 IALF 5021 : , "' ' QFT55 ; ' '. /. ' :•:', 11 v' '• , >H 1 1 il lC 1 MM |C& M \ |C& fvl |C 1 4 jM |c 0 2,000 4,000 6,000 8.000 10,000 Fig4 10,0001b-20,0001b, 44-5kN-89kN LF460 M45SDIRB.410D) RB.193••' •'/' "'/'•'/., FJR710/10, -", :.- i> 20 :S yi ' c c 4 M , 1 M45T1RB.424) \ Soev (RB.163 & RB.1681 :\\ M45SF (RB.415) CJ805-23B*'::; JT8D , 1 tin- iS; is:; m'Sti im"3< mi M45SE (RB.427I \ i 1 RB.199 ' ) M45BIRB.410) M53' "-"•C] ,'.' ' ' i ' JT3D ; ri: : r:: r : i So :S : i : c 1c tali 1 If [C* M |c :;: |c ::T']<D-: UklJ Ic |c «| 1 • ! •: ': . A M J,™ 'S r-^jw mm 0 5,000 10,000 15,000 20.000
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