Klimov VK-3 turbofan

[overscan (PaulMM)]

From http://www.missiles.ru/_foto/Klimov_muz/IMG_7412.jpg

 

[overscan (PaulMM)]

Was intended for Mikoyan I-3 (I-380) and I-3U (I-410) fighters. Designed by S V Lyunevich at Klimov, this was a bypass turbojet which first ran in 1952, and was qualified at 5,730kg dry and 8,440kg with afterburner in 1954. Serious development problems were encountered however which prevented the I-3 from flying.

 

[visvirtusvoluntas]

First afterburning turbofan in URSS, under development at OKB-117 since 1949. Designed for speeds up to 2000 km/h, estimated thrust 5160 kgp at nominal power, 6250 kgp at full military and 8400 kgp at full afterburner. Tested in I-3U in July 1956, good performances but poor reliability, modified in December 1956 with new compressor blades, ended his career in January 1958 alongside the airplane. Maybe "killed" by the less modern but more efficient Lyul'ka AL-7F.

 

[overscan (PaulMM)]

VK-3


In 1952, the bureau began to develop the first national turbofan VK-3 for the Mikoyan I-3 (I-380) interceptor. The engine was tested on the stand and in flight. During flight tests in 1956, it reached speeds of 1960 km/h and ceiling of 18,000 m.

By construction, the VK-3 - is a single-shaft turbofan with a 10-stage axial compressor (for the turbine bypass air carried by the second stage of the compressor to 12 pipes), an annular combustion chamber, a three-stage turbine, adjustable sash mixer, afterburner and variable supersonic nozzle. Compressor motor has two-position, adjustable inlet guide vanes eighth stage.

Standard engine produced.

Thrust, dry: 5730 kg
Thrust, afterburner: 8440 kg
SFC: 0.739
Weight: 1,850kg
T/W ratio: 4.56

http://www.propulsionplant.ru/content/55/dvigateli/aviacionnye-raketnye-morskie-promyshlennye/82178217zavod-imeni-v-ja-klimova82178217-gunpp