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Aviation History
1964
1964 - 2372.PDF
FUGHT International, 3 September 1964 379 [ t-l static rating no - — 150 _ 150 - 150 - 2 15 10 - : 10 20 50 05 30t 40f i iii i • a 40 ie e.h.p. — — — — _ — — — — — — — — — — — — 2,100 2,310 3,025 2,550 — — ~ 5,505 5,855 118 r.p.m. 3,200 3,200 n.a. 8,900 n.a. 26,750 n.a. n.a. 35.300 n.a. n.a. n.a. 10,000 10,000 n.a. 17,800 — 13.800 13,800 3,000 n.a. n.a. 8,050 8,050 8,150 2,750 2,700 3.200 10,140 n.a. 9,966 10,172 15,000 15.000 15,000 15.000 n.a. n.a. n.a. n.a. n.a. 12,490 12,530 12.390 n.a. 15,250 15,250 — 47,000 ..f.c n.a. n.a. n.a. n.a. n.a. 0.65 n.a. n.a. 0.68 n.a. n.a. n.a. 0.964 1.08 n.a. n.a. 0.495 n.a. 1.07 0.98 n.a. n.a. n.a. 0.786 0.853 0.802 — 0.735 n.a. 0.656 0.656 n.a. n.a. n.a. n.a. 0.560 0.612 n.a. 0.449 0.439 — 1.38 mass flow (Ib/sec) 783 cu in 1,118 cu in n.a. 196 n.a. 12.3 n.a. n.a. II n.a. n.a. n.a. 82 84 n.a. 24.5 n.a. 44 52.8 91.5 cu in n.a. n.a. 173 173 185 201 cu in 301 cu in 470 eu in 285 n.a. 367 375 23.5 27 27 16.8 16.2 16.6 n.a. n.a. n.a. n.a. n.a. 203 208 206 n.a. 46.5 46.5 365 + 178 1.38 press, ratio 6.5: 1 6.8 : 1 n.a. 13 n.a. 8.1 6 7 6.5 10.9 n.a. n.a. 4.4 4.4 n.a. 12.6 — 4.1 5.09 n.a. n.a. n.a. 9.1 9.35 10.3 7 7 8.6 14 n.a. 14.8 15.8 5.6 6.35 6.35 6.25 5.9 6.16 n.a. n.a. n.a. n.a. n.a. 16.8 16.9 19.1 n.a. 13.5 13.5 — 2.8 1 Thrust (Ib) — — 2,600 n.a. n.a. n.a. — n.a. n.a. n.a. n.a. n.a. n.a. — n.a. 1,190 875 — n.a. n.a. 2.420 3.920 4,680 65 103 188 4,625 n.a. 5.250 5,345 1,315 1,615 1,315 n.a. 2,960 3.070 3,070 3,070 n.a. 3,045 — — — Typii e.h.p. 360 550 — — 950 — 770 n.a. — 2.690 — — — n.a. n.a. — — — — — — — — — — — 100 »l cruise •.f.c 0.50 gal/hr 0.55 0.79 n.a. 0.602 n.a. n.a. 0.705 n.a. n.a. n.a. n.a. n.a. n.a. n.a. 0.499 n.a. 1.25 1.14 — n.a. n.a. 0.908 0.955 0.920 — — 0.822 n.a. 0.840 36,090 0.573 0.556 0.573 n.a. 0.748 0.763 0.764 0.770 n.a. 0.394 — 1.36 output alt (ft) 10.250 12.200 25400 — 10.000 — 5.000 60,000 n.a. 0 — 20,000 36,000 — n.a. n.a. 35,000 25,000 25,000 0 0 5,000 36,090 n.a. 36.090 36,090 20,000 20,000 20,000 n.a. 25,000 32,000 32.000 32,000 n.a. 25,000 — 0 Speed low low Mach ft ftU.O lOOkt — low Mach o "yJL.i. 0 — 500kt 420kt — n.a. n.a. 425 425 425 0 0 0 475 n.a. 475 475 300 300 300 n.a. 425 450 450 450 n.a. 320 — any Max appro- ved TBO (hr) 800 400 — — n.a. n.a. — 1,000 — — — — 4,100 2,600 2,200 1,200 1,200 600 6,500 1,200 4,800 E — 600 — 3.600 — — Customers RAF, home and overseas military and civil RAF, RN, various MoA Company project MoA, RAF MoA/RAE for WRE RAF, 14 civil and military RN MoA Army, RNL RAN. SAAF RAF RAF Airlines RAF Italy, W Germany, Greece, Turkey, etc MoA, W Germany, USA RAF US, Japan RAF, Sweden, Switzerland, Aus- tralia RAF, Australia, Italy, etc Civil and RAF Private RAF RAF Ten airlines Eight airlines Thirteen airlines Private Private Private Nine airlines RAF BOAC, BUA, Ghana RAF, BOAC More than 80 air- lines; more than I3( other operators RAF Japan RAF RAF RN. RAN RN RAF Germany Germany France, Germany, Italy For airlines BEA Seven airlines Four airlines RN RAF RCAF & six NATO MoA for ELDO Company proto- types Remarks Long-stroke version of earlier engine; described in this journal February 10, 1949. TBO trial to 1,000 hr Helicopter engine (Whirlwind Series 2) Tests began August 1962 Derived from BS.75 civil turbofan HS P. 1154, plenum-chamber burning, Mach 2 -f- Black Knight engine, derived from earlier version + Stertor Derived from GE T58, there is twin- ned version: described August IS. 1958 Buccaneer S.I; large bleed for aircraft systems Mach 3 power plant for Bristol T.I88 Also used in Westland air-cushion vehicle SK.N2 Superb record in Vulcan B.I; early engine described December 9, 1955 Vulcan B.2: further supersonic reheat 22R MK 320 for TSR.2 Concord powerplant; 60 : 40 shared with SNECMA Derated for long life in Gnat T.I FiatG.9l; similar engine in H.I26. Gnat F.I, etc; described November 22, 1957; also Indian reheat version for HF-24 Hawker Siddeley P.I 127 engine, air- cooled tlades, no PCB Blue Steel missile engine US design; turboprop versions; ratings conservative Bloodhound missile cruise engine; thrust is for early version Jet Provost T.4, Jindivik 3 drone; see issue dated December 20L 1962 HS.I25 and PD.808, Mystlre 20, etc Rollason Turbulent; also 30.7 h.p. version Lightning engine; Scimitar, Sea Vixen Lightning F.3 and 5; similar unit made by SFA for Draken 35D and later marks Comet 4, 4B and 4C; Avon 200 des- cribed October II. 1957 Caravel le 3 Caravelle 6, 6N and 6R; rating slightly reduced with reverser Identical to US-built engine Identical to US-built engine Identical to US-built engine: Beagle 206 Boeing 707-420 and Douglas DC-8-40; described January 15, I960 Victor B.2, uprated from RCo. 11 VCI0; new low-pressure assembly Super VC10 F-27 Herald, Argosy, Gulfstream. Viscount Argosy 660; w/m boost, cooled blades NAMC YS-II; w/m boost, cooled blades Andover; w/m boost, cooled blades Belvedere Wessex, Gazelle; described May 10, 1957 Hawker Siddeley 681 VJ 101C; joint development with MAN; 3,6501b with reheat EWR Siid VJ 101D: MAN jet deflector And ntDZzlfi Mirage HIV, VJ I0ID, Fiat G.222. VFW.I262, Dornier Do3l Fokker F-28 Fellowship Trident IC; described May 18, 1961 One-Eleven 200 Series One-Eleven 300 & 400 series, Trident IE; described May 2, 1963 Buccaneer S.2 and, with reheat, Phanf/im III v t4av l «J^^III 11 CL-44, Belfast (Vanguard similar); described April 22, I960Transall C.I 60, Breguet Atlantic; NATO-built Tested at 150,0001b thrust; twin instal- lation in Blue Streak; described August 17, 1961 Based on widely used 60 h.p. unit n*e to turbine flange where this applies, except for Gyrjn Junior DGJ.I0R where reheat pipe and nozzle is included; r.p.m. is compressor (gas-generator) speed;
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