RD-33 AFTERBURNING TURBOFAN ENGINE
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Full reheat power setting (H = 0, V = 0, ISA), kgf 8,300
Maximum nonreheat power setting (H = 0, V = 0, ISA), kgf 5,040
Specific fuel consumpton, kg/kgf.h 0.77
Bypass ratio 0.46
Maximum turbine inlet temperature, °K 1,680
Overall dimensions, mm:
length 4,230
maximum diameter 1,040
Weight, kg 1,055
[crossreferences: used by ]
MIG-29/MIG-35 Fulcrum Counter-Air Fighter
[crossreferences: armament ]
Russian Jet fuel data
The RD-33 engine is intended to power the MiG-29 fighter and its modifications.
The RD-33 is a double-flow two-shaft turbofan engine with flow mixing in a common afterburner. The engine is equipped with a fully-variable supersonic exhaust nozzle. Structurally, the engine comprises a four-stage low-pressure axial flow compressor, a nine-stage high-pressure axial flow compressor, a short annular combustion chamber, single-stage low- and highpressure turbines, an afterburner bypass air duct, and an adjustable exhaust nozzle.
The engine is provided with an electronic/hydromechanical control and monitoring system. The RD-33 is designed around a modular configuration. Owing to its high gasdynamic stability, the engine sets no limits on aircraft piloting and features a high rate of thrust buildup versus flight speed.
The following modifications were developed from the RD-33 engine: RD-33N to modernize foreign secondand third-generation single-engine fighters; RD-93 to power the latest FC-1 Chinese fighter.
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