In fact, Cheburashka is a double-hearted creature. His hearts are two D-36 engines, designed at ZMKB (an Ukrainian design bureau) by Lotarev et. al. Bench testing of D-36 began in 1971, flight testing under a Tu-16 in 1974 and series production in 1977.
D-36 became the base engine for the whole family: the D-136 turboshaft, D-236 propfan (demonstrator), D-336 industrial engine , and D-436K/T and D-436T1/T2 turbofans.
D-36 was also chosen to power Yak-42 aircraft.


D-36 DESCRIPTION

(click on the image to get full-screen drawing)

TYPE: Three-shaft turbofan.

FAN: Single-stage, transonic; 29 titanium blades with part-span shrouds; 48 outlet guide vanes (the number of blades and vanes chosen for minimum noise). Blade containment by winding Kevlar fibre on the fan casing. Maximum speed 5400 rpm. Mass flow 255kg/s.

LOW PRESSURE COMPRESSOR: Six stages with inlet guide vanes adjusted on the bench, then fixed in position. Three blow-off valves. Discs and rotor blades of titanium, stator vanes of steel. Maximum speed 10500 rpm.

HIGH PRESSURE COMPRESSOR: Seven-stage, with adjustable inlet guide vanes. Three blow-off valves. Rotor blades and disks of two aft stages of steel. Maximum speed 14170 rpm. Overall pressure ratio 18.7.

INTERMEDIATE CASE: Cast magnesium alloy. Forms connecting duct from low pressure compressor (LPC) to high pressure compressor (HPC) and bypass duct, and used for locating high pressure compressor front bearing and mounting LPC and HPC casings. Inside is a drive from HP rotor to accessory gearbox on intermediate case under nacelle cowl. The front engine mount is attached to the case.

COMBUSTION CHAMBER: Annular, with 24 burners and 2 igniters. Integral with HPT nozzle guide vanes (they form a single module). Combustion chamber case made by explosion stamping. Flame tube elements rolled and welded into one unit.

HIGH PRESSURE TURBINE: Single stage. Max. inlet 1137 degrees (Celsius). Rotor blades tip-shrouded, convective film-cooling system, attached by fir-free with two blades in each groove. Nozzle vanes have convective cooling.

LOW PRESSURE TURBINE: Single-stage. Uncooled, tip-shrouded, rotor blades. Nozzles guide vanes cooled by 3rd stage HPC air.

FAN OF LOW PRESSURE TURBINE: Three-stage with tip-shrouded blades, air-cooled discs.

EXHAUST UNIT: Consists of rear-bearing housing and main duct nozzle. Rear engine mount attached to housing.

CONTROL SYSTEM: Hydromechanical, with inner redundancy and electronic unit controlling gas temperature and rotor speeds. Compressor blow-off valves controlled by independent pneumonic (bubble memory) system located near the valves. Engine compressor air is the operating medium. The D-36 is provided with sensor sufficient for FADEC control.

STARTING: By air-turbine starter, on accessory gearbox, from ground source, APU or operating engine. Inflight starting can be assisted by starter.

COWLING: nacelle with common nozzle of fan and core ducts.

DIMENSIONS: length 3470 mm, diameter 1373mm.

WEIGHT, DRY: 1100 kg.

PERFORMANCE RATINGS: take-off static 63.74 kN, max cruise at 8000 m at Mach 0.75 15.7 kN.

SPECIFIC FUEL CONSUMPTION: take-off 10.195 mg/Ns, max cruise, as above 18.4 mg/Ns.