R-25-300 - aircraft turbojet twin-shaft two-stage engine, further development of the R-13-300 .
| P-25-300 | |
|---|---|
 P25-300 at the Karhulan ilmailukerho Aviation Museum ( Kotka , Finland ) | |
| Type of | turbojet |
| A country |  the USSR |
| Using | |
| Application | Mig-21 |
| Based on | P-13-300 |
| Production | |
| Constructor | S. A. Gavrilov |
| Year of creation | 1970 |
| Manufacturer | Ufa Plant No. 26 (now OJSC NPP Motor) |
| Years of production | 1972-1986 |
| Options | P25-300-94 |
| Weight and size characteristics | |
| Dry weight | 1215 kg |
| Length | 4615 mm |
| Diameter | 907 mm |
| Performance data | |
| Take-off thrust | 4100 kgf |
| Afterburner rod | 7100 kgf |
| Compressor | KND - axial, 3-stage, with high-pressure transonic steps KVD - axial, 5-speed |
| Turbine | TVD - axial, 1-stage, cooled TND - axial, 1-stage |
| Turbine temperature | 1057 ° C |
| The combustion chamber | tubular, 10 flame tubes |
| Degree of pressure increase | 9.55 |
| Air flow | 67.9 kg / s |
| Specific fuel consumption | take-off mode - 0.96 afterburning mode - 2.25 kg / kgf · h |
| Specific thrust | 5.8: 1 and 8.1: 1 on afterburner kgf / kg |
Content
Design
The engine consists of a 3-stage low-pressure compressor, 5-stage high-pressure compressor, a single-stage low-pressure turbine, a single-stage high-pressure turbine, a tube-annular combustion chamber, a two-stage afterburner and an unregulated jet nozzle.
Production and Operation
R-25-300 was developed at OKB-300 named after S.K. Tumansky , General Designer S.A. Gavrilov . It was produced at the Ufa engine-building software from 1972 to 1986 . Repair is carried out on; manufacturer, aircraft repair plant of the Ministry of Defense of the Russian Federation No. 218 and SE “Odessaaviaremservis” . The engine was mounted on a MiG-21 bis fighter, which significantly improved the maneuverability of the aircraft. At present, an engine modification is being developed - R-25-300-94 intended for installation on the MiG-21-93. P-25-300 is manufactured under license in India by HAL for installation on an Mig-21 bis Indian production.
Literature
- Zrelov V. A. Domestic gas turbine engines. The main parameters and design schemes. - Engineering, 2005 .-- S. 99, 100. - 336 p. - (For universities). - ISBN 5-217-03254-5 .
Links
- Description of the engine on the World Aviation Catalog website (Retrieved August 25, 2009)