Lotarev D-36

D-36
	D-36MV
Type	Turbofan
National origin	USSR
Manufacturer	Ivchenko-Progress; Motor Sich
First run	1971
Major applications	Antonov An-72; Antonov An-74; Yakovlev Yak-42
Developed into	Lotarev D-136; Progress D-436

The Ivchenko Progress D-36 (also known as Lotarev D-36) is a three-shaft high bypass ratio turbofan currently produced by the Ukrainian Motor Sich company.^[1]

Design and development[]

The engine was developed for the Yak-42, An-72 and An-74 aircraft and was very advanced when it was first introduced in the 1970s. The engine was designed by . The first test runs began in 1971, first flight tests followed in 1974, serial production began in 1977.

The engine has a single-stage fan with 29 titanium blades and a Kevlar outer shell, which is driven by a three-stage turbine. The six-stage with titanium blades is driven by a single-stage non-cooled low pressure turbine. The seven-stage high-pressure compressor with steel blades is driven by a steel bladed high-pressure turbine.

Since the tradition in the Soviet era was to gradually and continuously improve engines in serviceability, engines went from Series 1 to 3A (depending on the application). The Series 1 (used on Yak-42D) did not feature any reverse thrust system however, series 1A to 3A were fitted with bucket-type thrust reversers (used on An-72/An-74). The most recent upgrade (after the Soviet breakup) is Series 4A which has been in manufacture since 2002. Improvements included updated curved titanium blades and a built-in reverse thrust device. More advanced blade design along with proprietary wear-resistant and heat-protective coatings have resulted in improved specific fuel consumption (kg/h/kgf) dropping from 0.65 to 0.63. Specified service life has also improved exponentially to 40,000 hours. The current application for Series 4A is on An-74TK-300.

Specifications[]

Type	Thrust (kN)	Bypass Ratio at Start	Pressure Ratio	Fan Diameter (mm)	Length (mm)	Weight (kg)	Introduction	Application
Series 1	63.75	5.6:1	20:1	1,333	3,930	1124	1971	Yakovlev Yak-42
Series 1A/2A	63.75	5.6:1	20:1	1,333	3,192	1124	?	Antonov An-72 Antonov An-74
Series 3A	63.75	5.6:1	20:1	1,333	3,192	1124	?	Antonov An-74
Series 4A	63.75	5.6:1	20:1	1,333	3,732	1130	2002	An-74TK-300

Data from Élodie Roux,^[2] page 158

General characteristics

Type: 3-shaft turbofan
Length: 3.47 m (136.6 in)
Diameter: 1.333 m (52.5 in)
Dry weight: 1,109 kg (2,445 lb)

Components

Compressor: 7-stage high-pressure compressor, 6-stage low-pressure compressor
Turbine: 1-stage high-pressure turbine, 1-stage low-pressure turbine, 3-stage free-power turbine

Performance

Maximum thrust: Static sea level: 6,500.0 kgf (63.743 kN; 14,330 lbf); Cruise: 1,599.8 kgf (15.689 kN; 3,527 lbf) at Mach 0.75 speed, 8,001 m (26,250 ft) altitude
Overall pressure ratio: 18.7
Bypass ratio: 6.3
Air mass flow: 254.9 kg/s (562 lb/s)
Specific fuel consumption: Static sea level: 10.2 g/(kN⋅s) (0.36 lb/(lbf⋅h)); Cruise: 18.4 g/(kN⋅s) (0.65 lb/(lbf⋅h))
Power-to-weight ratio: