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Aviation History
1968
1968 - 0027.PDF
FLIGHT International, 4 January 1968 AERO ENGINES 1968 ... Gyron Junior Military single-shaft turbojet. Sole application is Hawker Siddeley Buccaneer SMkl. (Gyron Junior MklOl) Eight-stage compressor, annular combustor, two-stage turbine. Take-off 7,1001b; mass flow 1201b/sec; pressure ratio 6:1; length 121.lin; diameter 32.3in; weight 2,1001b. Orpheus Military single-shaft turbojets. In addition to BSE manu- facture, has been licence-built by Fiat, Klockner-Humboldt-Deutz and Hindustan Aeronautics. Applications Fairchild C-119G, IX Orpheus 701 (4,7001b). Fiat G.91, G.91R/1, G.91R/4 & G.91T, lxOrpheus 80302 (5,0001b); Fiat G.91R/3 & G.91T/3, lxOrpheus 803D Hll (5,0001b). Fuji T1F-2, lxOrpheus 805 (4,0001b). Hawker Siddeley Gnat Mkl, lxOrpheus 701 (4,7001b); Hawker Siddeley Gnat Tl, IxOrpheus 101 (4,5201b). (Orpheus 803) Seven-stage compressor, cannular combustor with seven flame tubes, single-stage turbine. Take-off 5,0001b; mass flow 841b/sec; pressure ratio 4.14:1; length 96.lin; diameter 32.4in; weight 9001b. Olympus Military twin-spool turbojet. Sole application is Hawker Siddeley Vulcan. Provided basis for Concorde engine. Applications Hawker Siddeley Vulcan B Mkl, 4 X Olympus MklOl (11,0001b) or MklO2 (12,0001b) or MklO4 (13,5001b). Hawker Siddeley Vulcan B Mk2, 4 X Olympus Mk201 (17,0001b) or Mk301 (20,0001b). (Olympus Mk301) Six-stage l.p. compressor, seven-stage h.p. com- pressor, cannular combustor with ten flame tubes, single-stage h.p. turbine, single-stage l.p. turbine. Take-off 20,0001b; mass flow 2901b/ sec; pressure ratio 13:1; length 13lin; diameter 44.5in; weight 4,2901b. Rolls-Royce Small Engine Division, Leavesden, Herts Gnome Civil and military free-turbine turboshaft. License-built Angicised version of General Electric T58. SED sub-licensed to Alfa-Romeo. Joint development by SED and GE to higher ratings. Latest SED version is 1,750 s.h.p. HI800 with increased mass flow zero-stage compressor and two-stage power turbine. Applications Agusta A101G, 3 X Gnome H1400 (1,500 s.h.p.). Agusta 205, 2 x Gnome H1200 (1,250 s.h.p.). Agusta-Bell AB204B, IX Gnome H1000 (1,050 s.h.p.) or Gnome H1200 (1,250 sJi.p.). Boeing-Vertol HKP-4, 2 x Gnome H1200 (1,250 s.h.p.). Westland Sea King, 2xGnome H1400 (1,500 s.h.p.). Westland Whirlwind 3, 9, 10 & 12, IX Gnome H1000 (1,050 s.h.p.). (Gnome H.1400) Ten-stage compressor, annular combustor, two- stage compressor-turbine, single-stage power-turbine. Integral rear- mounted gearbox. Take-off (5min) 1,500 sii.p.; length 54.8in; width 22.7in; height 21.6in; weight 3321b. (Coupled Gnome) Civil and military coupled free-turbine turbo- shaft. Comprises two Gnome engines coupled by common gearbox to provide single output drive. Applications Westland Wessex 2, 5, 51 & 60, lx Coupled Gnome H1200 (1,550 s.h.p.). Coupled Gnome H1200 Configuration similar to Gnome HI400 but with rear-mounted coupling gearbox. Maximum potential power 2,500 s.h.p. Nimbus Military free-turbine turboshaft. Based on Turbomeca gas generator technology. Sole applications are Westland Scout and Wasp with respectively IX Nimbus MklO5/5O2 (685 s.h.p.) and lxNimbus MklO3/5O3 (710 s.h.p.). (Nimbus Mkl03/503) Two-stage axial plus single-stage centrifugal compressor, annular combustor two-stage compressor-turbine, single- stage power-turbine. Integral rear-mounted gearbox. Take-off (5min) 710 s.h.p., ISA +25°C; mass flow HOlb/sec; pressure ratio 6:1; length 7,317in; width 38.7in; height 33.6in. SNECMA Societe Nationale d'Etude de Construction de Moteurs d'Aviation, Paris. M49 Larzac Civil and military twin-spool turbofan. A joint Snecma/Turbomeca project for a small, low s.f.c. turbofan for business and military liaison aircraft. (M49 Larzac) Two-stage fan, four-stage h.p. compressor, annular combustor, single-stage h.p. and l.p. turbines. Take-off 2,2601b; b.p.r. 1.5:1; mass flow 57.31b/sec; pressure ratio 9:1; length 56.5in; diameter 22in ; weight 4191b. M45A Civil twin-spool turbojet. A joint venture by Snecma and the Bristol Engine Division of Rolls-Royce, and based on the use of a common h.p. system throughout the M45 family of engines. 29 First run was at Snecma at the end of 1966, following which a thrust of 4,4101b was attained. Intended to power executive aircraft, no application yet announced. (M45A2) Four-stage l.p. compressor, seven-stage h.p. compressor, annular combustor, single-stage h.p. and l.p. turbines. Take-off 5,4551b; pressure ratio 14:1; length 802in; diameter 21.2m; weight 8821b. M45B Military twin-spool augmented turbojet. Military after- burning counterpart to the M45A. First run was at Snecma, early in 1967. Intended to power intercepters, no application has been announced. (M45B25) Configuration similar to that of M45A2 but with after- burner and variable convergent nozzle. Take-off 8,2251b with after- burner; pressure ratio 15:1; length 114.1in; diameter 21.2in; weight 1,2121b. M45F Civil twin-spool turbofan. Turbofan derivative of the M45A turbojet and intended for feeder-line aircraft, the M45F first ran in June 1966 at Snecma. No application yet announced. Military augmented counterpart, the M45G, will not proceed follow- ing cancellation of the Anglo/French VG project. (M45F3) Three-stage fan plus two-stage i.p, compressor (both driven by l.p. turbine), seven-stage h.p. compressor, annular com- bustor, single-stage h.p. turbine, two-stage l.p. turbine. Pressure ratio 14:1; length 71.5in; diameter 32in; weight 1,3601b. TF306 Military twin-spool augmented turbofan. Comprising the Pratt & Whitney TF30 turbofan with Snecma afterburner, the TF306 supersedes the similarly rated TF106 (comprising Snecma- developed version of the earlier JTF10A). Sole application is in the VG Dassault Mirage G with the TF3O6E. (TF306C) Three-stage fan plus six-stage i.p. compressor (both driven by l.p. turbine), seven-stage h.p. compressor, cannular com- bustor with eight flame tubes, single-stage h.p. turbine, three-stage l.p. turbine. Close-coupled afterburner with variable convergent- divergent nozzle. Take-off 19,8241b with afterburner; length 210in; diameter 47.2in; weight 3,7401b. Atar 9 Military single-shaft augmented turbojet. Essentially the Atar 8 with afterburning. Licensed manufacture by Sulzer in Switzerland and CAC in Australia. Latest version is the Atar 9K50 which first ran towards the end of last year. Applications Dassault Mirage 3A, B & C, lxAtar 9B (13,2771b with afterburning). Dassault Mirage 3E & R, lxAtar 9C (13,2771b with afterburning). Dassault Mirage 4, 2 X Atar 9K (14,7701b with afterburning). Dassault Mirage Fl, lxAtar 9K50 (13,2481b with afterburning). (Atar 9K) Configuration similar to that of Atar 8 but with addition of afterburner and variable nozzle. Take-off 10,3501b basic or 14,7701b with afterburning; mass flow 1581b/sec; pressure ratio 6.0:1; length 234in; diameter 40.1in; weight 3,2621b. Atar 8 Military single-shaft turbojet. Together with the after- burning Atar 9, comprises main series product of Snecma. Applications Dassault Etendard IV-M & P, lxAtar 8 (9,7001b). (Atar 8) Nine-stage compressor, annular combustor, two-stage turbine. Take-off 9,7001b; mass flow 1501b/sec; pressure ratio 5.5:1; length 153.5in; diameter 40.1in; weight 2,0391b. SOLOVIEV USSR D-30K Civil twin-spool turbofan. Increased b.p.r., higher-thrust version introduced to power second-generation Uyushin 11-62 in place of present Kuznetsov NK-8 turbofans. (D-30K) Three-stage fan, 11-stage h.p. compressor, cannular com- bustor with 12 flame tubes, two-stage h.p. turbine, four-stage l.p. turbine. Take-off 25,3501b; b.p.r. 2.3:1; pressure ratio 20:1; length 181.5in; diameter 61.4in; weight 4,7401b. D-30P Civil twin-spool turbofan. Developed to power the Tupolev Tu-134. (D-30P) Four-stage fan, ten-stage h.p. compressor, cannular combustor, two-stage h.p. and l.p. turbines. Take-off 14,9901b; b.p.r. 1:1; pressure ratio 18.6:1; length 154.7in; weight 3,3501b. Angh/'French associations are again evident in the R-R Bristol Engine Division/Snecma M45H, which has been selected for the VFW 614 airliner
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