FlightGlobal.com
Home
Premium
Archive
Video
Images
Forum
Atlas
Blogs
Jobs
Shop
RSS
Email Newsletters
You are in:
Home
Aviation History
1965
1965 - 0048.PDF
3.2 FLIGHT International 7 January I96S AERO ENGINES single-shaft turbojets. This advanced engine is fitted with a Hamilton Standard control system which automatically governs the variable intake, fuel supply and variable-area nozzle. The JT12 (military J60), designed by United Aircraft Canada, is a small 3,0001b turbojet which powers the JetStar and Sabreliner. The JT12A-21 prototype achieves 4,0251b with reheat. A JFTD12 rear drive turboshaft version has been developed from the JT12, and two 4,050 s.h.p. JFTD12A-3s power the Sikorsky S-64 Skycrane. The US Navy-sponsored TF30-P-1 (JTF10A-20) is a high- compression two-spool turbofan developed for the F-111A and B. With fully modulated afterburning in both hot and cold flows, maximum thrust will exceed 19,0001b. An early version, probably a 10,5001b JTF10A-7 was flight tested under a B-45. The cycle is a two-stage fan plus 14 compressor stages, 8-can-annular combustion system and four-stage turbine. Pressure ratio is 16 :1. SNECMA are producing a TF316 afterburning development of the JTF10, for the Mirage HIV. The STF-200C turbofan, under study for the C-5A (CX-HLS), started static running last April. With a by-pass ratio of 2, it develops 31,0001b unaugmented at sea level and weighs about 5,5001b. The two-stage large-diameter front fan is driven by a three-stage low-pressure turbine, while a two-stage high-pressure turbine drives the nine-stage compressor. Already under con- sideration is the STF-200D with a by-pass ratio of 3 and about 36,0001b thrust without augmentation. The STF-200F, an even more advanced development with a by-pass ratio of 4, would have an unaugmented thrust of about 39,0001b, and an s.f.c. of about 0.66 at Mach 0.8 and 30,000ft. Diameter would be more than 7ft, length about 9£ft and weight about 6,6001b. Titanium is extensively used. SOLAR Solar (Subsidiary of International Harvester Company), San Diego, California. The Solar 80 h.p. T62 Titan has been used to power one-man helicopters, and is installed as an a.p.u. in a number of military aircraft and helicopters. USSR A variety of successful engines has been produced to the designs of Ivchenko under the AI designation. Seven- and nine-cylinder radials from 260 to 300 h.p. power a number of helicopters and utility aircraft. Ivchenko's design bureau is also responsible for the majority of Russia's turboprop transport engines. Ten-stage, axial compression, automatically controlled AI 20s of 4,000 e.h.p. power the An-10 and 11-18, and 2,535 h.p. AI 24s the An-24. ASH radials, evolved by A. D. Shvetsov from early Wright and P & W designs, are still widely used in the Communist countries, in transports and helicopters. Mikulin turbojets under the designation M209 (RD3 and AM3) have also appeared outside Russia in the ubiquitous Tu-104 series; large numbers of Mikulin Mil five-cylinder radials have been built in Russia and Poland, to power light aircraft and helicopters. Pratt & Whitney JT8D Pratt & Whitney J58 JT\l) N. D. Kuznetsov's design team specializes in very large turbines. The 21,0001b thrust NK8 turbofan powers the 11-62, and the 14,795 e.h.p. NK12M turboprop, the most powerful in existence, with a fourteen-stage axial compressor and five-stage turbine, drives the 18ft 4in diameter contra-rotating propellers of the Tu-114, and Bear bomber. The rotor weighs about one ton, maximum compression ratio is 13 :1, and mass flow is reported to be 1371b/sec. S. K. Tumanskii is responsible for the Tye 29 lightweight turbo- jets which have been used in record attempts by the Yak-30 and 32. Ratings are reported to be 1,875 and 2,3151b thrust for the Yak-30 engine, and 1,7641b for the Yak-32. Soloviev's design team is reported to be responsible for the 11,0001b thrust turbofans fitted in the Tu-124, the first Soviet transport to employ such powerplants. The rear-engined Tu-134 is also, presumably, similarly powered. Soloviev engines in the 30,0001b class dry (45,0001b with reheat) are believed to be installed in the inboard positions of the mixed turbofan/turbojet four- engined Bounder. The same team has developed the 4,635 s.h.p. TB2BM and 5,622 s.h.p. TB2 turboshafts, which respectively power the Mi-6 helicopter and the Kamov Ka-22 Vintokryl convertiplane. The late V. Y. Klimov's design team developed the Rolls-Royce Nene, along much the same lines as Rolls-Royce themselves, to the VK1, Russian equivalent of the Tay. More than 20,000 of this 7,5901b thrust afterburning turbojet were built in the late 1950s for early Mig fighters and 11-28 bombers. A similar quantity of VK5 (or M205) axial flow turbojets in the 6,5001b class (8,8181b with reheat) has been produced for the Mig-19 and Yak-25. Two type 37V turbojets of the same output, and possibly VK5s under another designation, were fitted to the RV aircraft which set up two payload-to-height records in 1959. The VK7 small diameter axial flow turbojet, comparable in size with the Bristol Siddeley Orpheus 12 and rated at 6,7001b thrust dry, is said to be a develop- ment of the VK5 and was at one time regarded as a possible powerplant for the production version of the Hindustan HF-24. There are, of course, several engines of design origins unknown outside Russia. Two 14,3301b thrust turbojets designated Type AL-7PB power the Beriev M10 flying-boat. The 28,6601b thrust D15 turbojet is one of the most powerful yet known to have flown. Four of these engines were fitted in the 103M and 201M aircraft, which set up a number of closed-circuit and payload to height records in 1959. The E66, believed to be a developed Mig-21, and another speed and height record holder of 1959-61, was fitted with a 13,1171b thrust R37F turbojet. The prefix R may indicate reheat, and the engine is possibly a development of the VK5, M205 or 37V referred to above. The record breaking E66A was also fitted with a 6,6151b thrust GRD Mk U2 rocket motor. PI 66 is the designation given to the 22,0461b thrust turbojet fitted in the delta wing E166 which holds the world's absolute speed record. The same rating is quoted for the TRD31 turbojet fitted in the T431 aircraft, implying that the designation is related to the aircraft in which the engine is installed. TRD Mk P166 and TRD31 are presumably versions of the same turbojet. The 400 s.h.p. turboshafts fitted in the Mil V2 helicopter, have been designated GTD35O in Soviet record claims, and are reported to have been designed by a team led by S. Izotov. The Russians must be credited with the world's smallest piston radial—if reports via America are correct of the existence of VP760. This is a very small 22 h.p. five-cylinder radial, with a cubic capacity of 46.4 cu in and a dry weight of 531b, which has allegedly been designed for use iu powered gliders, ultra-light aircraft and helicopters.
Sign up to
Flight Digital Magazine
Flight Print Magazine
Airline Business Magazine
E-newsletters
RSS
Events
