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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 afterburning 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 1,800 mph (2,900 km/h), and a maximum takeoff weight of 101,000 lb (45,800 kg). These powerful engines also allowed the large and complex fighter to attain supersonic speeds at low altitudes under 5,000 feet (1,500 m).
The D30-F6 is used on a variety of Russian, Chinese, and other Eastern European airliner and military transport designs. The massive Aviadvigatels have only been used in two 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: 57.3 in (1.46 m)
- Dry weight: 5082 lb (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: 0.498 lb/lbf·hr
- Thrust-to-weight ratio: 3.8:1
- 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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