Lyulka AL-21
The Lyulka AL-21 is an air jet engine that was developed in the USSR by Archip Mikhailovich Lyulka from the early 1960s as the successor to the AL-7 and manufactured in large-scale production from 1967. Up to 1991, 5011 copies were built in Plant No. 45 in Moscow .
The standard version AL-21F-3 is a single-shaft jet engine with a 14-stage axial compressor with guide vanes that were adjustable in the 1st to 4th and 10th to 14th stages. The turbine blades of the first two stages of the three-stage turbine were cooled by diverted air from the compressor. The combustion chamber was a tubular ring combustion chamber with 12 nozzles.
AL-21 versions
- AL-21F - version for the Tu-128
- AL-21F-3 - Version from 1970 for the MiG-23 B, Su-22 and Su-24 as well as T-10 and Su-17
- AL-21F-3A - Version for Su-17M and Su-24M
photos
Lyulka AL-21
Lyulka AL-21 F3
Data Lyulka AL-21 F3
Lyulka AL-21 F3
Lyulka AL-21 F3
Technical specifications
- Starting thrust with afterburner: 110 kN
- Starting thrust without afterburner: 76.5 kN
- Max. Speed: 11,150 / min
- Turbine inlet temperature: 1370 ° C
- Max. Air flow: 104 kg / s
- Compression: 14.75: 1
- Weight (dry): 1800 kg (1580 kg for Al-21F)
- Diameter: 1.03 m
- Length: 5.34 m
Web links
Commons : Lyulka AL-21 - Collection of images, videos and audio files
swell
- ↑ Ulf Gerber: The great book of Soviet aviation 1920–1990 . Rockstuhl, Bad Langensalza 2019, ISBN 978-3-95966-403-5 , p. 374 .
- ↑ Aircraft Engines ( Memento of the original from March 16, 2012 in the Internet Archive ) Info: The archive link was inserted automatically and has not yet been checked. Please check the original and archive link according to the instructions and then remove this notice.
- ^ Lyulka AL-21
- ↑ al-21f (Russian)
