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

RD-36-51
RD-36-51 installed on a Tu-144 aircraft
Type	Turbojet
National origin	Soviet Union
Manufacturer	Kolesov Design Bureau
Major applications	Tupolev Tu-144

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 modification with a fixed nozzle for the high-altitude Myasishchev M-17 was designated RD-36-51B. The engine develops 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)
• Mass = 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—a modification of the RD36-51A engine with an unregulated nozzle and oxygen supply to the combustion chamber. The engine provides long-term 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 are released in a small series (about 50 pieces).

Variants

RD-36-41

Created on the basis of the engine 'VD-19' .[2]

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

• 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-36-51)

General characteristics

• Type: Turbojet
• Length:
• Diameter:
• Dry weight:

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
• Specific fuel consumption: 35 g/(kN·s)) 1.23 lb/(lbf·h)[4]
• Power-to-weight ratio:

See also

Comparable engines

• Rolls-Royce/Snecma Olympus 593

Related lists

• List of aircraft engines

References

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На других языках

[fr] Kolesov RD-36-51

[ru] РД-36