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Aviation History
1968
1968 - 0028.PDF
30 FLIGHT International, 4 January 1968 The Turbomeca Astazou II has been built in large quantities. The latest application is the Anglo- French Sud SA.34O light observation helicopter AERO ENGINES 1968 . . . D-25V (TB-2BM) Civil and military free-turbine turboshaft. Power unit for the Mil Mi-6, Mi-10 and Mi-IOK helicopters. (D-25V) Nine-stage compressor, cannular combustor with 12 flame tubes, single-stage compressor-turbine, two-stage power-turbine. Direct drive. Take-off 5,500 e.h.p.; pressure ratio 5.6:1; length 107.75in; weight 2,6451b. D-20P Civil twin-spool turbofan. Introduced to power the Tupolev Tu-124. (D-20P) Three-stage fan, eight-stage h.p. compressor, cannular combustor, single-stage h.p. turbine, two-stage l.p. turbine. Take-off 11,9051b; b.p.r. 1:1; mass flow 2491b/sec; pressure ratio (overall.) 13:1; length 130in; diameter 38.3in; weight 3,2401b. TURBOMECA (Societe Turbomeca) Bordes, Basses-Pyrenees, France Oredon III Civil and military single-shaft turboshaft. Launched as a joint project by Turbomeca and the Small Engine Division of Rolls-Royce, the Oredon III is based on Astazou technology. First run was at Turbomeca in autumn 1966. No application has been announced for the turboshaft, or for the equivalent turboprop project. (Or£don III) Two-stage axial plus single-stage centrifugal com- pressor, annular combustor, three-stage turbine. Integral front- mounted gearbox. Take-off 350 s.h.p.; pressure ratio 7.5:1; length 42in; diameter 14in; weight 179.51b. Aubisque Civil and military geared front-fan turbofan. Prime application is the Saab 105 with two Aubisque lAs. (Aubisque 1A) Single-stage fan gear-driven off front of com- pressor, single-stage axial plus single-stage centrifugal compressor, annular combustor, two-stage turbine. Take-off 1,6351b; mass flow 49.01b/sec; pressure ratio 6.9:1; length 81.4in; diameter 21.6in; weight 5861b. Astazou Civil single-shaft turboprop. Now in its third generation of development, is in competition with the AiResearch TPE331 and United Aircraft of Canada PT6A. Latest version is the 921 e.h.p. Astazou XIVC, being flight tested in a modified Morane-Saulnier MS-1500 Epervier. Applications Dornier Do27 T-l, 2 X Astazou II (562 e.h.p.). Handley Page Jetstream, 2 X Astazou XIVC (921 e.h.p.). Israel Aircraft Arava, 2 x Astazou XII (731 e.h.p.). Pilatus PC-6/A1-H2 Turbo-Porter, lx Astazou XII (731 e.h.p.). Potez 842B, 4 x Astazou XII (731 e.h.p.). Short Sky van Series II, 2 X Astazou XII (731 e.h.p.). (Astazou XIV) Two-stage axial plus single-stage centrifugal com- pressor, annular combustor, three-stage turbine. Integral front- mounted gearbox. Take-off 921 e.h.p.; pressure ratio 8:1; length 69in; diameter 18in. Astazou II Civil and military single-shaft turboshaft. Second generation counterpart to Astazou turboprop with prime application in the Sud-Aviation Alouette II helicopter. Applications Sud-Aviation Alouette II Astazou, lx Astazou II (554 e.h.p.). Sud-Aviation SA. 240, lx Astazou II (530 s.h.p.). (Astazou II) Single-stage- axial plus single-stage centrifugal com- pressor, annular combustor, three-stage turbine. Integral front- mounted gearbox. Take-off 554 e.h.p.; mass flow 5.51b/sec; pressure ratio 6:1; length 50.1in; diameter 18.1in; weight 2691b. Bastan Civil single-shaft turboprop. Third generation turboprop with the Nord 262 as its prime application. Application Nord 262, 2 X Bastan VIC (1,065 e.h.p.) or Bastan VII (1,400 s.h.p.). (Bastan VIIA) Two-stage axial plus single-stage centrifugal com- pressor, annular combustor, three-stage turbine. Integral front- mounted gearbox. Take-off 1,400 s.h.p.; mass flow 13.lib/sec; pressure ratio 6.68:1; length 75.2in; diameter 3O.5in; weight 5951b. Marbore Civil and military single-shaft turbojet. Installed in numerous light strike/trainer aircraft. Powers also French and American target drones, for the latter being license-built and developed by Continental as the J69. Applications Hispano HA-200E Super Saeta, 2xMarbor6 VI (1,0581b). Nord CT20 Version IV, lxMarbor6 II (8801b). Nord CT20, 1 X Marbord VI (1,0581b). Potez CM170 Magister, 2 x Marbort II (8801b). Potez CM Super Magister, 2 x Marbore VI (1,0581b) Potez 94, 2 X Marbore Super VI (1,1701b). Potez MS760A Paris I, 2 X Marbore II (8801b). Potez MS760B Paris II, 2 x Marbore VI (1,0581b). Potez MS760C Paris III, 2 X Marbore VI (1,0581b). (Marbore VI) Single-stage centrifugal compressor, annular com- bustor, single-stage turbine. Take-off 1,0581b; mass flow 21.61b/sec: pressure ratio 3.84:1 ; length 55.74in; width 23.35in; height 24.82in: weight 3091b. Tunno Civil free-turbine turboprop. Third-generation turboprop with the Breguet 941S as its prime application (4xTurmo III D3). (Turmo III D3) Two-stage axial plus single-stage centrifugal compressor, annular combustor, two-stage compressor-turbine, two- stage power-turbine. Integral rear-mounted and forward-mounted gearboxes. Take-off 1,430 e.h.p.; mass flow 131b/sec; pressure ratio 5.5:1; length 75.6in; width 37.0in; weight 6941b. Tunno Civil and military free-turbine turboshaft. Second- generation turboshaft counterpart to Turmo turboprop. Applications Sud-Aviation Super Frelon, 3 X Turmo IIIC3 (1,500 s.h.p.). Sud-Aviation SA.330, 2XTurmo III C4 (1,282 s.h.p.). (Turmo III C4) Single-stage axial plus single-stage centrifugal compressor, annular combustor, two-stage compressor-turbine, two- stage power-turbine. Integral rear-mounted gearbox. Take-off 1,282 s.h.p.; mass flow 13.01b/sec; pressure ratio 5.8:1; length 71.6in; width 27.3in; height 28.2in; weight 5001b. Artouste Civil and military single-shaft turboshaft. Highly success- ful helicopter turboshaft, powering the Sud-Aviation Alouette. More than 700 engines delivered. Applications Sud-Aviation Alouette II, 1 X Artouste IIC5 (de-rated to 360 s.h.p.) or Artouste II C6 (de-rated to 360 s.h.p.). Sud- Aviation Alouette III, lx Artouste III B (de-rated to 550 s.h.p.). (Artouste HI B) Single-stage axial plus single-stage centrifugal compressor, annular combustor, three-stage turbine. Integral front- mounted gearbox. Take-off 870 s.h.p.; mass flow 9.51b/sec; pressure ratio 5.2:1; length 71.46in; width 19.96in; height 24.68in ; weight 2871b. UNITED AIRCRAFT OF CANADA Longueuil, Quebec JT15D Civil and military twin-spool turbofan. First run September 1967 and scheduled to start flight testing this year, the JT15D is intended to power business, transport and military aircraft in the 7,0001b to 12,5001b class. The gas generator section embodies com- ponent technology from the company's PT6 turboprop/turboshaft. With certain modifications the present configuration, rated at 2,0001b, could be developed to give 3,0001b. (JT15D) Single-stage fan, single-stage centrifugal h.p. compressor, annular reverse-flow combustor, multi-stage h.p. and l.p. turbine. Take-off 2,0001b; b.p.r. 3.2:1; length 50in; diameter 27in; weight 4901b. PT6A Civil and military free-turbine turboprop. Scheduled for a wide variety of applications, the PT6 (and industrial ST6) has been the sole turbine of UAC prior to the advent of the JT15D. Unique by virtue of its "back-to-front" installation with the compressor fed via an integral plenum chamber. Over 1,600 engines built. Latest version is the 751 e.h.p. PT6A-27. Applications Beech King Air A90 & VC-6A, 2XPT6A-20 (550 s.h.p.). Commuter Lines U-21A & NU-8F, 2XPT6A-20 (550 s.h.p.). De Havilland of Canada Turbo-Beaver, 1XPT6A-6 (550 s.h.p.). De Havilland of Canada Twin Otter, 2XPT6A-20 (550 s.h.p.). Fairchild Hiller/Pilatus Heli-Porter, 1XPT6A-20 (550 s.h.p.). Helio Stallion, 1XPT6A-20 (550 s.h.p.). McKinnon Goose, 2XPT6A-20 (550 s.h.p.). Swearingen Merlin IIA, 2XPT6A-20 (550 s.h.p.). (PT6A-27) Three-stage axial plus single-stage centrifugal compressor, annular reverse-flow combustor, single-stage compressor-turbine, single-stage power-turbine. Integral front-mounted gearbox. Take-off 751 s.h.p.; mass flow 6.61b/sec; pressure ratio 7:1; length 62in; diameter 19in ; weight 2891b. PT6B Civil free-turbine turboshaft. Turboshaft counterpart to PT6A turboprop. Applications Lockheed XH-51A, 1 X PT6B-9 (550 s.h.p.). Lockheed Model 286, 1 XPT6B-9 (550 s.h.p.). (PT6B-9) Similar in configuration to PT6A. Take-off 550 s.h.p. T74 Military free-turbine turboshaft. Military counterpart to PT6A turboprop. Experimental installation in North American OV-10A.
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