• Source: Kolesov RD-36

The Kolesov RD-36 was a supersonic turbojet engine used on various Soviet aircraft projects.




Design and development


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:

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


RD-36-41
Created on the basis of the engine 'VD-19' .
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. It is recognizable by the translating-plug variable-area nozzle.
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). 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


Tupolev Tu-148 (RD-36-41)
Sukhoi T-4 (RD-36-41)
Tupolev Tu-144D (RD-36-51A)
Myasishchev M-17 Stratosphera (RD-36-51B)




Specifications (RD-36-51A)





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)




See also



Comparable engines

Rolls-Royce/Snecma Olympus 593
Related lists

List of aircraft engines




References

Kata Kunci Pencarian:

• Kolesov RD-36-51
• Kuznetsov NK-144
• Tupolev Tu-144
• Turbojet
• Kolesov RD-36
• Rybinsk RD-36-35
• Kolesov
• Tupolev Tu-144
• Kuznetsov NK-144
• UEC Saturn
• Sukhoi T-4
• Myasishchev M-55
• Plug nozzle
• Rolls-Royce/Snecma Olympus 593