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Aviation History
1970
1970 - 0037.PDF
, FLIGHT International, I January 1970 * (RB.193-12) Three-stage fan/l-p compressor, two-stage i-p com pressor, six-stage h-p compressor, annular combustor, single-stage h-p three-stage 1-p turbine. Separate thrust-vectoring nozzles for cold and hot flows. Take-off 10,1701b; b.p.r. 1.12:1; mass flow 2031b/sec; pressure ratio 16.2:1; length 96in; diameter 37.6in; weight 1,7411b. RB.1S3 Military two-shaft turbofan. Rated at 6,8501b, has been developed as a joint project by MTU and Rolls-Royce to power the erstwhile EWR-Sud VJ101D V/STOL fighter. Used in develop ment of afterburner and thrust-vectoring systems. (RB.153-61) Four-stage fan/l-p compressor, twelve-stage h-p com pressor, cannular combustor, two-stage h-p and 1-p turbines. Take-off * 6,8501b; mass flow 1211b/sec; pressure ratio 18:1; length 89in; diameter 29.5in; weight 1,4301b. DB 730 (ZTL6) Civil and military free-turbine aft-fan turbofan. Uses DB 720 as gas generator with DB 721 compressor first-stage f as aft-fan. Originally developed by Daimler-Benz as private venture. Also is DB 730H proposed by D-B for high-speed compound heli- t copters by providing inter-turbine switch-in gas bleed to energise remote turbine driving helicopter rotor. At lift-off DB 730H I 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) centri fugal 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. 6022 Civil and military single-shaft turboshaft. An exceptionally simple, low-power shaft turbine primarily for helicopter installations. Applications Bolkow B6105 (prototype), 2 X Model 6022 A2 (250 s.h.p.) Bolkow B6105 (production), 2 X Model 6022 A3 (375 s.h.p.). ' Dornier Dol32, lx Model 6022 B2 hot gas generator (440 h.p.). Dornier System Aerodyne, 1 X Model 6022 A2 (350 s.h.p.). < (Model 6022 A2) Single-stage centrifugal compressor, annular com bustor, single-stage turbine. Integral front-mounted gearbox. Take-off 250 s.h.p. to ISA+13°C; weight 1871b. 6012L Civil and military single-shaft air generator. Comprises a i 6012A turboshaft with separate front-mounted single-stage com pressor driven from the front of the engine. Applications Dornier Do32, lxModel 6012 L2 ri.l61b air/sec). Dornier Do 32K Kiebitz, lx Model 6012 L3 (1.241b air/sec). , (6012-L) Single-stage centrifugal air generator (mounted on front of engine and directly driven), single-stage centrifugal compressor, annular combustor, single-stage centrifugal turbine. Take-off 1.321b/ sec at 2.5:1 air-generator; pressure ratio; compressor pressure ratio 3:1; length 29.9in; diameter 14.96in; weight 971b. DB 721 (PTL10) Civil and military free-turbine turboshaft. Under development in both turboshaft and turboprop forms. Latest version ^j 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; i pressure ratio 6:1; length 91.3in; diameter 19.1in; weight 5501b. DB 720 (PTL6) Civil and military free-turbine turboshaft. f 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) com pressor, 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. MOTORLET * Motorlet NC. Headquarters: Prague, Czechoslovakia. Titan Military' two-shaft turbofan. Military derivative of Ivchenko i AI-25 civil turbofan being developed under licence by Motorlet to power Czechoslovak Aero L-39 trainer. Is also known as Walter Titan. Initial AI-25W Motorlet version is rated at 3,30001b, to be followed by improved 3,9601b AI-25WM with two-stage fan and f air-cooled h-p turbine. A projected third version is rated at 4,4001b. M-701 Military single-shaft turbojet. Sole example of Czecho- » Slovak turbojet, powers single-engined L-29 Delphin for which more than 4,500 M-701s have been built. t (M-701C-500) Single-stage centrifugal compressor, can-type com bustor with seven flame tubes, single-stage turbine. Take-off 1,9621b; mass flow 37.251b/sec; pressure ratio 4.3:1; length 81.38in; width 35.28in; height 36.53in; weight 7281b. i M-601 Civil free-turbine turbofan. Under development to power version of Czechoslovak Let L-410 twin-engined transport for sale > to Eastern-bloc countries. (United Aircraft of Canada PT6A to power L-410s for Western countries.) Seven M-601s built and one test flying in modified Ilyushin 11-14. Growth potential to 730 e.h.p. (M-601) Two-stage axial plus single-stage (single-sided) centrifugal compressor, annular combustor, single-stage compressor and power •» turbines. Back-to-front installation with rear plenum intake, and front-mounted integral gearbox. Take-off 550 e.h.p. (initial version), 700 e.h.p. (revised version); mass flow 6.lib/sec (initial version), 6.81b/sec (revised version); pressure ratio 6:1 (initial version), 6.2:1 (revised version); length 60.2in; diameter 12.4in (initial version), 16.9in (revised version); weight 3311b (initial version), 2981b (revised version). ORENDA Orenda Ltd (joint company of Hawker Siddeley Canada Ltd and United Aircraft Corporation). Headquarters: Malton, Ontario, Canada. Orenda is licence-manufacturing the US General Electric J8S augmented turbojet as the 4,3001b J85-CAN-15 for Canadian-built Northrop CF-5 fighters. The company also overhauls J79, J85 and Orenda turbojets and is engaged in sub-contract work for Pratt & Whitney Division, UAC and other US companies. PIAGGIO Aero Engine Division, Industrie Aeronautiche e Meccaniche Rinaldo Piaggio, SpA. Divisional Headquarters: Genoa, Italy. The Aero Engine Division of Piaggio has been engaged in licenced- manufacture of the 2,5001b Rolls-Royce Viper 11 turbojet to power Aermacchi MB.326 trainers and in 1965 sub-licensed the engine to the Atlas Aircraft Corporation for South African-built MB.326 Impala trainers. In March 1969 a licence was signed with R-R for manufacture of the 3,3601b Viper Mks 540 and 526 to power the MB.326 and the Piaggio-Douglas PD-808. The company also licence-manufactures the 1,400 s.h.p. Lycoming T53-L-13 turboshaft for the Agusta-Bell 204B and 205B. PRATT & WHITNEY Pratt & Whitney Aircraft Division (United Aircraft Corporation). Divisional headquarters: East Hartford, Connecticut, USA. F100/F401 Military two-shaft augmented turbofan. Competing engine with US General Electric F100/F400 (q.v.) to power F-15 and Grumman F-14B USAF and USN air-superiority aircraft. With the company designation JTF22 the new turbofan, with an afterburning rating of approximately 29,0001b, has been under test at P&W's Florida Research & Development Centre at West Beach, Florida, since July 1969. The demonstrator programme is jointly funded by the USAF and USN with the US Air Force executive agency. JTF20 Military two-shaft augmented turbofan. Competing engine with US General Electric GE9 (q.v.) to power the USAF's B-1A advanced manned strategic aircraft (AMSA). Technology understood to be based on experience with earlier JTF16 augmented turbofan, with development proceeding at P&W's Florida R&D Centre. JTF16B Military two-shaft augmented turbofan. First run in late autumn 1966 under USAF funding as one of two competing turbo- fans originally to power AMSA, the JFT16B is rated at approxi mately 10,0001b basic, rising to about 20,0001b with duct-burning. The engine is also concerned in P&W's development of a vectored- thrust cruise propulsion engine under USAF contract. Thrust vec toring is provided by means of an aft-hood exhaust deflector enabling the full augmented thrust to be deflected through 90". Version of JTF16 rated at 13,0001b comprised P&W's losing entry in MRCA-75 engine competition during 1969. Turbofan Project Civil two-shaft turbofan. Pratt & Whitney and Rolls-Royce in late 1969 submitted initial proposals for 25,0001b turbofans to power three- or four-engined Boeing Model 767 medium-range large-capacity/long-range low-capacity transport pro ject. Long-term sales are estimated at around 500 aircraft equiva lent to an engine market in excess of $1,200 million (£500 million). Problems with the 747 entry into service are likely to delay a decision by Boeing to proceed with 767. Quiet Engine Civil two-shaft turbofan. Pratt & Whitney and US General Electric are participating in NASA's Quiet Engine Pro gramme, and prototype engine design proposals have been submitted to the Administration. A basic feature of both companies' designs is a single-stage fan on its own rotor. Potential applications All Boeing 707/720 series and Douglas DC-8 series aircraft. (P&W Quiet Engine) Single-stage fan, 12-stage h-p compressor, annualar combustor, two-stage h-p turbine, five-stage 1-p turbine. Take-off 22,0001b; b.p.r. 5.4:1; length 118in; diameter 68.8in; weight approximately 6,9001b. JT9D Civil two-shaft turbofan. Under development and in pro duction for the Boeing 747 and McDonnell Douglas DC-10-20, the JT9D is the world's first large civil turbofan. First run in December 1966 followed by flight testing in a modified B-52 in June 1968, the JT9D powered the 747 on its first flight in February 1969. Certification of the 43,5001b JT9D-3 was completed in May 1969 and the engine was scheduled to have entered service in late 1969. Problems with engine carcass distortion, thrust deficiency and over-guarantee s.f.c. are delaying service until January 1970. Higher thrust versions under development include the 45,0001b
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