FlightGlobal.com
Home
Premium
Archive
Video
Images
Forum
Atlas
Blogs
Jobs
Shop
RSS
Email Newsletters
You are in:
Home
Aviation History
1968
1968 - 0022.PDF
24 FLIGHT International, 4 January I96i AERO ENGINES 1968... (T53-L-13) Five-stage axial plus single-stage (single-sided) centri- fugal compressor, annular reverse-flow combustor, two-stage com- pressor-turbine, two-stage power-turbine. Take-off 1,400 s.h.p., dia- meter 23.0in; weight 5301b. T53 Military free-turbine turboprop engine. Propeller turbine ver- sion of T53 turboshaft. Applications Grumman OV-1 Mohawk, 2XT53-L-3 (1,005 e.h.p.) or T53-L-7 (1,150 e.h.p.). (T53-L-7) Similar configuration to T53-L-13 except for single-stage compressor-, power-turbines. Take-off 1,150 e.h.p.; military rating 1,046 e.h.p. and 0.661b/e.h.p./hr; mass flow 10.71b/sec; pressure ratio 6:1; length 58.4in; diameter 23.0in; weight 5551b. MAN TURBO Munich, West Germany RB.193 Military vectored-thrust twin-spool turbofan. Rated at 10,0001b, is being developed as a joint project by MAN and Rolls- Royce under a £8 million contract from the West German Ministry of Defence. Sole application is VFW VAK-191B V/STOL fighter. Flight engines are scheduled to be delivered this year. RB.1S3 Military twin-spool turbofan. Rated at 6,8501b, has been developed as a joint project by MAN 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. turbine, two-stage l.p. turbine. Take-off 6,8501b; pressure ratio 18:1; length 89in; dia- meter 29.5in; weight 1,4301b. RB.145 Military lift/cruise single-shaft turbojet. Collaborative de- velopment by Rolls-Royce and MAN to power the EWR-Sud VJ101C V/STOL research aircraft. Comprises RB.108 lift jet with zero-stage compressor and has afterburner. (RB.145) Nine-stage compressor, annular combustor, two-stage turbine. Close-coupled afterburner with simple variable convergent nozzle. Take-off 2,7501b basic, 3,6501b with afterburning; pressure ratio 5.7:1; length 50in; diameter 15.5in; weight 4571b. 6022 Civil and military single-shaft turboshaft. An exceptionally simple, low-power shaft turbine primarily for helicopter installations. Applications Bolkow Bo 105, IX Model 6022A2 (250 S.h.p.). Dornier Dol32, lx Model 6022. (Model 6022A2) Single-stage centrifugal compressor. Annular com- bustor, single-stage axial 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 6012A turboshaft with separate front-mounted single-stage com- pressor driven from the front of the engine. Sole application is the Dornier Do32 helicopter. (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. The Pratt & Whitney JT9D powerplant for the 490-seat Boeing 747 MICROTURBO France Fclair Single-shaft turbojet. Based on Microturbo APU technology, is an ultra-small turbojet for use in sailplanes and drones. Sole application is Fauvel AV.45-01 tailless self-launching sailplane. (Eclair) Single-stage centrifugal compressor, annular reverse-flow combustor, single-stage turbine. Take-off 1761b; length 26.5in; dia- meter 12.3in; weight 77.11b. MIKULIN USSR AM-3M Civil single-shaft turbojet. Developed from early Mikulin M-209 military turbojet. Is notably the most powerful turbojet in commercial operation. Applications TupDlev Tu-104A, 2xAM-3M (19,1801b). Tupolev Tu-104B, 2XAM-3M-5OO (21,3851b). (AM-3M-500) Eight-stage compressor, cannular combustor with fourteen flame tubes, two-stage turbine. Take-off 21,3851b; pressure ratio 6.4:1; length 210.03in; diameter 55.12in. MOTOROLET Czechoslovakia M-701 Military single-shaft turbojet. Sole example of Czecho- slovak turbojet, powers single-engined L-29 Delphin of which more than 1,000 have been built, and proposed for new twin-engined L-39 advanced military trainer/strike aircraft. (M-701) Single-stage centrifugal compressor, can-type combustor 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. PRATT & WHITNEY (Pratt & Whitney Aircraft Division, United Aircraft Corporation), East Hartford, Connecticut, USA STF300 Civil twin-spool turbofan. Project study for a 50,000 to 60,0001b turbofan to power second-generation Boeing 747s. JT18D Civil twin-spool turbofan. Derivative of the JT9D scaled- down and optimised on 35,0001b thrust to power Douglas DC-10 and Lockheed L-1011 in competition with General Electric CF6/34 and Rolls-Royce RB.211. (JT18D) Single-stage fan plus three-stage i.p. compressor (both driven by l.p. turbine), eleven-stage h.p. compressor, annular com- bustor, two-stage h.p. turbine, four-stage l.p. turbine. Take-off 35,OOOlb; b.p.r. 5:1; mass flow l,1811b/sec; pressure ratio (overall) 24:1; length 116.0in; diameter 85.10in; weight 6,5201b. ST9 Military turboshaft. Designed under contract to US Army Aviation Material Laboratories, and entering two-year demonstrator phase in competition with counterpart General Electric project. Rated at 1,500 s.h.p., the ST9 appears to have axial/centrifugal com- pressor, reverse-flow annular combustor, and multi-stage turbine. JT9D Civil twin-spool turbofan. Being developed as a private venture to power the Boeing 747, the JT9D is notably the most powerful civil turbofan in existence. Design is based on advanced technology of JTF16 and of JTF14, losing P&W entry for the C-5A. Original JT9D-1 was up-rated to 42,0001b and will power the 747 during its initial flight testing in December this year. A further request by Boeing for increased thrust is met by the 43,5001b JT9D-3 flight testing of which in a modified Hoeing B-52E will start in June. Certification of JT9D-3 is scheduled for March 1969 with production engines being delivered the following month. Price of JT9D-3 is $800,006 and production will reach 40 per month. Snecma, which is developing an alternative design of h.p. com- pressor, signified in June last year that it intends to exercise its option on a licence to manufacture the JT9D. Applications Boeing 747, 747C, 747F and 747P, 4XJT9D-3 43,5001b). Lockheed L-500-114M and L-500-114Q, 4XJT9D-7 (45,5001b). Lockheed L-500-114P and L-500-114R, 4XJT9D (47,5001b). (JT9D-3) Single-stage fan plus three-stage i.p. compressor (both driven by l.p. turbine), eleven-stage h.p. compressor, annular com- bustor, two-stage h.p. turbine, four-stage l.p. turbine. Take-off 43,5001b; b.p.r. 5:1; mass flow l,6001b/sec; pressure ratio 24.5:1; length 128in; diameter 96in; weight 8,4301b. JTF16B Military twin-spool augmented turbofan. First run in late autumn 1966 under USAF funding as one of two competing turbo- fans to power AMSA, the JTF16B is rated at approximately 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 vector- ing is provided by means of an aft-hood exhaust deflector enabling the full augmented thrust to be deflected through 90°. Other poten- tial applications include FX, VFAX and the US/FRG AVS, m which together with AMSA the compsting General Electric engine is the GE1/10.
Sign up to
Flight Digital Magazine
Flight Print Magazine
Airline Business Magazine
E-newsletters
RSS
Events
