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Aviation History
1965
1965 - 0040.PDF
25 FLIGHT International, 7 January AERO ENGINES trainer. Orpheus 701 and 703 turbojets are being made under Bristol Siddeley licence, respectively for the Gnat Fl and HF-24 Maruta Mk 1. Further licence agreements enable HAL to manufacture Dart 531 turboprops for the IAF-built HS 748s, and Artouste 2Cs for licence-built Alouette 2s. Italy AGUSTA Agusta Meccanica Verghera SA, Gallarate. Agusta have produced a range of horizontally-opposed piston engines from 40 to 140 h.p., a flat twin and a flat four suitable for light aircraft, and two vertical-crankshaft fours for helicopters. Reduction gears and other components are also produced for the Turbomeca-Agusta TM251 (TAA 230) turboshaft for the A. 105. ALFA ROMEO Milan. Alfa Romeo are overhauling Wright radials and J65 turbojets, Rolls-Royce Darts, Avons and Conways, and Bristol Siddeley Gnomes. They also share with Fiat, FN and BMW in production of GE J79-11A turbojets for the F-104G and are Italian distributors for GE J85 and CJ610 turbojets. FIAT Fiat SpA, Turin. Some 200 Orpheus 803 turbojets (Fiat designation 4023 and 4024), have been made since 1960 under Bristol Siddeley licence for the G.91. In collaboration with Alfa Romeo, FN and BMW, Fiat manufacture and assemble the GE J79-11A for the F-104G. Fiat also provide overhaul and service support for a variety of piston engines and earlier turbojets. Fiat have developed a variety of small units from their own 4002 turbojet. The 4700 vertically mounted gas generator was made for the Fiat 7002 cold-jet helicopter, now abandoned. A shaft-drive version, the 4301 and the 4004 turbojet have also been built. METEOR Meteor SpA, Costruzioni Aeronautiche, Trieste. Meteor have produced a series of small two-stroke, single-row, four-cylinder, and two-row, eight-cylinder, radial piston engines which range in power from 120 to 320 h.p. All versions are basically similar, with common components, and are less than 23.6in in diameter. Scavenging is by Rootes type blower. Some are rated for target drone applications, with a power/weight ratio of 0.851b/h.p.; others are certificated for light aircraft, with a TBO of l,000hr. Various models are rated to maintain constant power up to 8,000, 20,000 or 26,000ft, and one target drone version is capable of operation at 32,000ft. Vertical crankshaft versions are also available. PIAGGIO Rinaldo Piaggio SpA, Genoa. Piaggio's engine division continue with licence production and service support of a variety of Lycoming flat six piston engines. They are also manufac- turing the BS Viper 22-1 turbojet under licence for the Macchi MB.326 trainer. Japan IHI Ishikawajima-Harima Heavy Industries Co Ltd, Aircraft Engine Division, Kitatama-Gun, Tokyo. Under licence from General Electric, IHI manufacture J79-11A turbojets for the F-104J, and T58 turboshafts for helicopter and other applications. Of IHI's own design is the J3-7, a simple 3,0001b thrust axial flow turbojet intended for the Fuji TIB trainer, and the J3-F, a 3,7501b turbofan version with a rear-mounted large-diameter, single-stage free turbine fan. The XJ11, scheduled to complete its performance tests during 1964, is being developed as a V/STOL powerplant. IHI also have a contract from the Aeronautical Engineering Institute of the Science and Technology Agency to manufacture the prototype of an experimental turbojet designated JR100. This is the first of three stages of a four-year development programme for a V/STOL aircraft engine with a thrust-to-weight ratio of 20 : 1. The initial JR100, due for delivery last October, has a six-stage axial flow compressor, mainly steel parts in compressor and turbine, and a 10 :1 thrust/weight ratio at 3,1531b thrust. This will be improved to 15:1 when steel is replaced by light alloy in the compressor, and titanium in the turbine. The second JR100, to be BMW 6022 250 h.p. turboshaft delivered this year, is expected to achieve a thrust/weight ratio of 18 :1. The third engine should have the 20 : 1 ratio in 1966. Poland OKL Osrodek Konstrukeji Lotniczych, Warsaw-Okecie. Few details are known of the two small turbojets developed by the jet engine design team of OKL, which was established in 1957. The 8821b thrust TO-1 is a centrifugal flow turbojet for light aircraft. An axial flow engine of about 2,0001b thrust, thought to have a seven-stage compressor, annular combustion chamber and single- stage turbine, has been produced for the T5-11 Iskra trainer. Narkiewicz-designed piston engines developed by OKL for Polish light aircraft and helicopters include the 330 h.p. WN3 seven-cylinder radial, the 68 h.p. NP1 and 125 h.p. WN7 flat fours, the geared 145 h.p. WN7R and the 195 h.p. WN6B flat six, develop- ing 220 h.p. as the geared WN7R, and 200 h.p. for helicopters as the WN6S. OKL makes a number of Russian-designed turbojets and radial piston engines under licence, including the Klimov VK1 and 1A turbojets (Polish LIS2A and 5), for the Polish Air Force. Spain ENMA Empresa Nacional de Mot ores de Aviacion SA, Madrid. ENMA continues to produce its own 93 h.p. Flecha flat four, 125 h.p. Tigre inverted in-line four, and the 275 h.p. Alcion geared supercharged, seven-cylinder radial. The Turbomeca Marbore 2 is made under licence, as the Marbore M21, for the Hispano Saeta. Sweden SFA Svenska Flygmotor AB, Trollhattan. RM6C is the desig- nation of the Rolls-Royce Avon 301 turbojet being produced under licence and fitted with an SFA-designed afterburner and nozzle, for the Saab Draken. Maximum thrust approaches 17,0001b. Lack of British Government support at the time for development of the Rolls-Royce Medway forced the Royal Swedish Air Board to turn to the USA for the powerplant for the Saab 37 Viggen. This will be the RM8, a licence-built development of the P & W JT8D-22 turbofan, which will be extensively modified for supersonic perfor- mance and fitted with a Flygmotor-developed afterburner, variable nozzle and reverser. United Arab Republic HELWAN Helwan Air Works. Furthering their bid for status and some degree of independence in military aviation, the United Arab Republic is developing a small 7,0001b thrust afterburning turbojet as part of the HA-300 fighter programme. Designated E300; this engine, which is dimensionally similar to the Bristol Siddeley Orpheus, is being built to the design of Prof Brandner, an Austrian who also contributed to the development of the Kuznetsov NK12M and other Soviet turbines. The E300 was expected to fly in 1964, and may further be flight tested in the Indian HAL HF-24 Maruta as a possible powerplant for the supersonic Mk 2.
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