2 0 FLIGHT International, 2 January 1969

A E R O E N G I N E S 1 9 6 9 . . .

BOEING (Turbine Division, The Boeing Company), Seattle, Washington, USA Model 502/T50 Military free-turbine turboshaft. Sole propulsion role is powering Gyrodyne QH-50C US Navy drone helicopter. (Model 502-10VC/T50-BO-8A) Single-stage (single-sided) centrifugal compressor two-can straighMhrough flow combustor, single-stage compressor-turbine, single-stage power-turbine. Integral rear-mounted gearbox. Military rating 300 s.h.p.; mass flow 4.221b/sec; pressure ratio 4.63:1; length 40.48in; width 43.52in; height 28.15in; weight 3341b. Model S50/T50 Military free-turbine turboshaft. Improved deriva­tive of Model 502. Powers solely Gyrodyne QH-50D drone helicop­ter. (Model 550-1/T50-BO-12) Single-stage axial plus single-stage (single-sided) centrifugal compressor, two-can reverse-flow com­bustor, single-stage compressor-turbine, single-stage power-turbine. Integral rear-mounted gearbox. Maximum rating 365 s.h.p.; mass flow 4.41b/sec; pressure ratio 5.8:1: length 37.5in; width 40.24: height 22.5in; weight 2671b.

B U D W O R T H David Budworth Ltd, Harwich Puffin Civil turbocompressor. Under development as power unit for VFW H-3 twin-engined compound helicopter. Comprises gas turbine drive for integrally-mounted compressor supplying air to cold fix-jet rotor and/or air-turbine driven cruise fans. Puffin provides continuous 200 s.h.p. to compressor.

C O N T I N E N T A L (Gas Turbine1 Division, Continental Aviation and Engineering Corporation), Detroit, Michigan, USA J69 Military single-shaft turbojet. Based on Turbomeca Marbore and Gourdon, has both drone and manned aircraft applications. Over 3,700 engines built. Latest version is J69-T-41A (1,9201b). Applications Cessna T-37A, 2XJ69-T-9 (9201b). Cessna T-37B & T-37C, 2XJ69-T-25 (1,0251b). Ryan BQM-34A Firebee 1, 1XJ69-T-29 (1,7001b) or 1XJ69-T-41A (1,9201b); BQM-34E Firebee II, 1XJ69-T-6 (1,8401b). (J69-T-29) Single-stage axial plus single-stage (single-sided) centri­fugal compressor, annular reverse-flow combustor, single-stage turbine. Take-off 1,7001b; mass flow 28.61b/sec; pressure ratio 5.5:1; length 44.8in; width 22.36in; height 24.83in; weight 3401b. Model 356 Civil free-turbine aft-fan turbofan. Reported to be under development as an aft-fan version of the J69, using the turbojet as gas generator. Model 356-16 is rated at 2,6001b and Model 356-24 at 4,0001b. Model J100-CA-100 Turbojet, rated at 2,7001b for a weight of 4051b, the J100 has a mass flow 44.51b/sec and pressure ratio of 6.3:1. T67 Military coupled free-turbine turboshaft. Comprises two T72 engines coupled by common gearbox to provide output drive. Applications Augusta A109B, 1XT67-T-1 (1,540 s.h.p.). Bell Model 208 Twin Delta, 1XXT67-T-1 (1,400 s.h.p.). (T67-T-1) Two-stage axial plus single-stage (single-sided) centrifugal compressor, annular reverse-flow combustor, two-stage compressor turbine, single-stage power-turbine. Integral front-mounted coupling gearbox. Maximum rating 1,700 s.h.p.: pressure ratio 7.5:1, length 52in; width 38in; height 21in; weight 5401b.

DAIMLER-BENZ Stuttgart-Untertiirkheim, West Germany DB 720 (PTL6) Civil and military free-turbine turboshaft. Scheduled for flight testing in modified Bell UH-1D helicopter under contract to German Ministry of Defence. (DB 720) Four-stage axial plus single-stage (single-sided) compres­sor, annular combustor, two-stage compressor turbine, single-stage power-turbine. Integral rear-mounted gearbox. Take-off 1,330 e.h.p.; mass flow 13.51b/sec; pressure ratio 5.5:1: length 78.5in; height 28.35in; width 20.3in; weight 4851b. DB 721 (PTL10) Civil & military free-turbine turboshaft. Under development in both turboshaft and turboprop forms. Latest version being developed at 2,400 e.h.p. Supported by government finance. (DB 721) Eight-stage compressor, annular combustor, two-stage compressor-turbine, single-stage power-turbine. Non-integral front-mounted gearbox. Take-off 2,200 e.h.p.; mass flow 221b/sec; pressure ratio 6 :1 ; length 91.3in; diameter 19.1in; weight 5501b.

Selected to power the US Navy's VSX anti-submarine aircraft, the General Electric {USA) TF34 twin-spool turbofan is rated in the 9,0001b bracket. It owes much to the development of the TF39

DB 730 (ZTL6) Civil & military free-turbine aft-fan turbofan. Uses DB 720 as gas generator with DB 721 compressor first-stage as aft-fan. Under development as Daimler-Benz private venture. Also is DB 730H proposed by D-B for high-speed compound heli­copters by providing inter-turbine switch-in gas bleed to energise remote turbine driving helicopter rotor. At lift-off DB 730H provides 1,600 s.h.p. to rotor, changing to 2,2051b thrust in forward (autorotational) flight. (DB 730F) Four-stage axial plus single-stage (single-sided) centri­fugal compressor, annular combustor, two-stage compressor-turbine, single-stage fan-turbine, single-stage aft-fan. Take-off 2,2501b; b.p.r. 5.5:1; mass flow (total) 81.61b/sec; pressure ratio (gas generator) 5.5:1, (fan) 1,295:1: length 88.6in ; diameter 20.3in.

EGAO Egyptian General Aero Organisation, Helwan, Egypt E 300 Civil single-shaft augmented turbojet. Designed and developed at Helwan by German engineers as replacement for Rolls-Royce Orpheus in Helwan HA-300 supersonic fighter. Has been test flown in Antonov An-12 and Hindustan HF-24 Marut. Civil versions of E 300 are also proposed. Applications Helwan HA-300, 1X E 300-A (7,2751b basic and 10,5801b with afterburning). (E 300-A) Nine-stage compressor, can-annular combustor with ten primary heads and annular rear section, two-stage turbine. After­burner with continuously variable convergent nozzle. Take-off 7,2751b basic and 10,5801b with afterburner; mass flow 1181b/sec; pressure ratio 6 :1 ; length 169.3in; diameter 33in; weight 1,8961b. E 300 Civil single-shaft turbojet. Commercial counterpart to military E 300 proposed for development. Basic versions are the 6,6151b E 300-C1 and 7,4951b E 300-C2 growth version. Higher r.p.m., higher mass flow derivatives are the 8,5101b E 300-PX and 9,2801b E 300-PX/W with water-mefhanol injection. EGAO/ Messerschmitt Project 206 powered by three E 300C-ls is sole application. (E 300C-1) Similar configuration to E 300-A without afterburner. Take-off 6,6151b; mass flow 1181b/sec; pressure ratio 6 :1 ; length 98.4in; diameter 33in; weight 1,6311b. E 300 Civil free-turbine aft-fan turbofan. Projected turbofan variant of E 300-C2 turbojet. (E 300-AF) Similar configuration to E 300-C1 but with addition of single-stage free-turbine driving single-stage aft-fan. Take-off 10,1401b; b.p.r. 1.5:1; mass flow (overall) 2941b/sec; length 118.lin; diameter 47.2in; weight 1,8741b.

F L Y G M O T O R (Svenska Flygmotor), Trollhatan, Sweden RM8 Military twin-spool augmented turbofan. Licensed version of Pratt & Whitney JT8D-22 civil turbofan, is being developed by Flygmotor as supersonic afterburning engine for SAAB 37 Viggen Mach 2 intercepter and strike fighter. Under a government 689 mil­lion Sw Kr development and production contract, 195 RM8s are being built. (RM8) Two-stage fan plus four-stage i-p compressor (both driven by 1-p turbine), seven-stage h-p compressor, cannular combustor with nine flame tubes, single-stage h-p turbine, three-stage 1-p turbine. Flygmotor afterburner, multi-flap variable primary nozzle with ejector, three-petal thrust reverser, fixed area secondary nozzle. Take-off 16,0001b basic, 26,4501b with afterburning; b.p.r. 1:1; mass flow 3201b/sec; pressure ratio (overall) 16.5:1; length 118.lin; diameter 55.lin; weight 4,6301b.