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|National origin||Soviet Union|
|Manufacturer||Soloviev Design Bureau|
|Major applications||Mikoyan MiG-31
The Soloviev D-30 is a Soviet two-shaft low-bypass turbofan engine, officially referred to as a "bypass turbojet." A supersonic afterburner version, the D-30F6, is used in the Mikoyan-Gurevich MiG-31 interceptor, while the non-afterburning civilian versions, the D-30Kp and D-30KU are used in the Ilyushin Il-62M and Tupolev Tu-154M airliners, and in the Ilyushin Il-76MD, TD heavy cargo aircraft.
Design and development
In the mid-1970s, the Soviet Union began the search for a high-speed interceptor to supplement and replace its MiG-25. The Mig-25 had two enormously powerful Tumansky R-15 turbojets, allowing Mach 3 speed at high altitudes, but the problem was their weak performance at low altitudes, not even sufficient to cross Mach 1 boundary. More acute problems stemmed from the tendency of the Foxbat's engines to break down at maximum throttle in high-speed situations. A new engine, this time a low-bypass turbofan, was needed to power the new interceptor. The Mikoyan-Gurevich (MiG) design bureau contracted OKB-19 design bureau (now part of Aviadvigatel) to build such an engine, for the aircraft that would become known as the MiG-31.
Aviadvigatel came up with the D30-F6 turbofan. Capable of generating 9,500 kgf (20,900 lbf or 93 kN) dry thrust and 15,500 kgf (34,200 lbf or 152 kN) afterburning thrust, the engine gave MiG's new fighter a top speed exceeding 3,000 km/h (1,900 mph), and a maximum takeoff weight of 45,800 kg (101,000 lb). These powerful engines also allowed the large and complex fighter to attain supersonic speeds at low altitudes under 1,500 m (4,900 ft).
The D-30 is used on a variety of Russian, Chinese, and other Eastern European airliner and military transport designs[specify]. The massive Aviadvigatels have only been used in two fighter aircraft designs: the MiG-31 Foxhound, and the experimental Sukhoi Su-47 Berkut (formerly S-37).
Data from 
- Type: Twin-spool non-afterburning turbofan
- Length: 4.836 m
- Diameter: 1.455 m
- Dry weight: 2305 kg
- Compressor: Axial, 3 stage fan/low pressure compressor, 11 stage high pressure compressor
- Combustors: Can-type
- Turbine: 2 stage high pressure turbine, 4 stage low pressure turbine
- Maximum thrust: 23,150 lbf (103 kN)
- Overall pressure ratio: 17:1
- Specific fuel consumption: 0.790 lb/(lbf·h)
- Thrust-to-weight ratio: 3.8:1
- Comparable engines
- Related lists
- Barron 1980, pp. 169–171.
- Gas Turbine Engines. Aviation Week & Space Technology Source Book. pg. 122.
- Jane's All The World's Aircraft 1995
|Wikimedia Commons has media related to Soloviev D-30.|
- D-30F6 description at manufacturer's site
- D-30KP description at manufacturer's site (for Il-76)
- D-30KU description at manufacturer's site (for Il-62M)
- D-30KU-154 description at manufacturer's site (for Tu-154M)
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