Kolesov RD-36
 | This article needs additional citations for verification. (May 2024) |
| RD-36-51 | |
|---|---|
| |
| View of variable area plug nozzles as fitted for engines in the TU-144D | |
| Type | Turbojet |
| National origin | Soviet Union |
| Manufacturer | Kolesov Design Bureau |
| Major applications | Tupolev Tu-144 |
The Kolesov RD-36 was a supersonic turbojet engine used on various Soviet aircraft projects.
Design and development
[edit]Developed at OKB-36 (P. A. Kolesov) and produced at the Rybinsk Motor-Building Plant, the RD-36-51A engine was developed for the Tu-144D supersonic passenger aircraft. A simplified version with a fixed nozzle for the high-altitude Myasishchev M-17 was designated RD-36-51B. The engine developed a thrust of 7,000 kgf (15,000 lbf; 69,000 N). The RD36-51A engine passed all state bench and flight tests in 1973–75 (with flight testing on the Tu-144D).
The engine's specifications were:[1]
- Maximum thrust at take-off = 20,000 kgf (44,000 lbf; 200,000 N)
- Maximum thrust during supersonic cruise = 5,000 kgf (11,000 lbf; 49,000 N) altitude = 18,000 m (59,000 ft), speed = 2,350 km/h (1,460 mph)
- Maximum thrust during subsonic cruise= 3,000 kgf (6,600 lbf; 29,000 N) altitude = 11,000 m (36,000 ft), speed = 1,000 km/h (620 mph)
- Temperature = 1,355 K (1,082 °C; 1,979 °F)
- Diameter = 1,486 mm (58.5 in)
- Length = 5,976 mm (235.3 in)
- Weight = 3,900 kg (8,600 lb)
For the high-altitude M-17 "Stratosphera" aircraft (NATO reporting name Mystic-A) a single-shaft TRD RD36-51B was created. This was a modified version of the RD36-51A engine with an unregulated nozzle and oxygen supply to the combustion chamber. The engine provided long-duration operation at an altitude of 26,000 m (85,000 ft) at low flight speed (M = 0.6).
- P = 7,000 kgf (15,000 lbf; 69,000 N)
- With beats. vsl. = 0,88 kg / kgf • h.
RD-36-51A / B was produced in a small series (about 50 units).
Variants
[edit]Thrust – 16,150 kgf (35,600 lbf; 158,400 N)
- RD-36-51
- This engine was a replacement for the Kuznetsov NK-144 turbofan used on the Tu-144D SST, giving an increase in full payload range from 3,080km to 5,330km.[3] It is recognizable by the translating-plug variable-area nozzle.[4]
- RD-36-51A
- The RD-36-51A produced 20,000 kgf (44,000 lbf; 200,000 N) thrust at take-off and had a cruise thrust-specific fuel consumption of 1.22 kg/(kgf. h).[3] which gave the aircraft a maximum range of 6,500 km.
- RD-36-51B
- Non-afterburning turbojet for use in high-altitude reconnaissance/research aircraft, such as the Myasishchev M-17 Stratosphera.
Applications
[edit]- Tupolev Tu-148 (RD-36-41)[2]
- Sukhoi T-4 (RD-36-41)
- Tupolev Tu-144D (RD-36-51A)
- Myasishchev M-17 Stratosphera (RD-36-51B)
Specifications (RD-36-51A)
[edit]General characteristics
- Type: Turbojet
- Length: 5.976 m (235.3 in)
- Diameter: 1.486 m (58.5 in)
- Dry weight: 3,900 kg (8,600 lb)
Components
- Compressor: Axial
Performance
- Maximum thrust: 24,000 kgf (53,000 lbf; 240,000 N) at takeoff and 5,400 kgf (12,000 lbf; 53,000 N) cruise
- Overall pressure ratio: 16.1
- Specific fuel consumption: 35 g/(kN·s)) 1.23 lb/(lbf·h)[4]
See also
[edit]Comparable engines
Related lists
References
[edit]- ^ Gordon, E.; Gordon, Yefim; Komissarov, Dmitriy; Rigmant, Vladimir (2015). Tupolev Tu-144: The Soviet Supersonic Airliner. Schiffer Publishing, Limited. ISBN 978-0-7643-4894-5.
- ^ a b "Aviation and Cosmonautics" No. 9–10 / 2001 // V. Rigmant "Long-range supersonic anti-aircraft fighters Tupolev interceptors "
- ^ a b Tupolev Tu-144, Gordon, Komissarov and Rigmant 2015,Schiffer Publishing Ltd., ISBN 978-0-7643-4894-5, p.248
- ^ a b PSC «Tupolev» - TU-144 Archived 2008-09-20 at the Wayback Machine
 |
This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |