D-30F6

In the mid-1960s, new models of strategic and offensive weapons appeared: cruise missiles capable of flying at extremely low altitudes, enveloping the surface of the earth, high-altitude and high-speed reconnaissance aircraft, strategic bombers and other types of weapons. To protect the long borders of the USSR from these and other threats, an aircraft was needed with the ability to detect and intercept targets from low altitudes to 30 kilometers, at speeds up to 4000 km / h, which could carry various types of missiles to intercept and destroy air targets at extremely small , small, medium and high altitudes, accompany several targets at the same time. In addition, due to the low density of air defense and airfields in the Far East and the north of the country, the aircraft should have a large radius of action.

For such an aircraft, unique in its properties, it required a no less unique engine of high power with high efficiency. The Perm Motor Engineering Design Bureau (ICD, now Aviadvigatel OJSC) under the leadership of P. A. Solovyov was tasked with making this engine. Soloviev decided to make a dual-circuit engine with an afterburner with a mixture of flows of the external and internal circuits of the engine.

At that time, there were many opponents of such a scheme, since engines according to such a scheme had not yet been produced.

Initially, a demonstration engine was created on the basis of the D-30 serial engine equipped with an afterburner. After a series of tests at the TsIAM stand, the correctness of the choice of engine layout became apparent, and in 1970 ^{[1] the} ICD began developing the D-30F6 engine for an interceptor fighter. A prototype aircraft with this engine took off in 1975 ^[2] .

The engine has unique high-speed characteristics, providing a maximum aircraft speed of 3,000 km / h and ground speed of 1,500 km / h.

The D-30F6 engine is of a modular design, made of 7 modules. All modules (except the base) can be replaced in operation. Engine Modules:

• Input guide vane
• low pressure compressor
• Base module:
  • Separation housing
  • High pressure compressor
  • The combustion chamber
  • High pressure turbine
  • Low pressure turbine
  • Back support
• Mixer body
• Afterburner
• Jet nozzle
• Front and rear drive unit block

Reliability of the engine is provided by systems of protection, duplication and early detection of malfunctions:

• a system for limiting the maximum rotational speed of a low pressure rotor and a system for limiting the maximum gas temperature behind a turbine;
• a system of protection against the spin of a turbine drive a constant speed;
• anti-icing system for the cowl and vanes of the inlet guide vane of the low-pressure compressor;
• anti-surge system.

The electronic-hydraulic system of automatic engine control in case of failure of the electronic system is duplicated by a hydraulic system that ensures flight safety and task performance. The engine design provides the ability to parametric control of its condition on the plane. To assess the state of the gas-air duct parts during operation, the engine design provides for the inspection of all compressor working blades and turbines, as well as nozzle blades of the 1st and 2nd stages of the turbine. In the event of foreign objects getting into the gas-air path of the engine, the design allows replacing in operation both individual damaged blades of the 1st stage of the compressor and the entire low-pressure compressor module.

• D-30KU-154

• D-30F6 on the site of Aviadvigatel OJSC
• D-30F6 on the site of the aviation encyclopedia " Corner of the sky "
• D-30F6 - Website of the Diesel Engineers of St. Petersburg State Technical University