Sunday, July 29, 2012

D-436TP and D-30KP Turbojet Engine

D-436TP Turbojet Engine

The D-436TP turbofan features a three-shaft configuration with minimum number of bearing supports. It has a modular design. The transonic fan is of a single-stage type. The low-pressure compressor has six stages, and the high-pressure compressor has seven stages. The engine has an annular combustion chamber. The lowpressure turbine is single-staged, and the highpressure turbine is three-staged. The engine is equipped with a thrust reverser, an electronichydromechanical control system and universal
attachment fittings.

D-436TP Turbojet Engine

The D-436TP turbofan engine is designed for the Be-200 aircraft. It boasts high reliability ensured by a longtime operating experience of the D-36 engine. is easy to maintain, and can be operated in sea
environment. The engine demonstrates stable operation in spite of sharp air inflow temperature inversions during forest fire-fighting missions. The engine complies with standing and future ICAO noise and emission requirements.

D-436TP Specifications
Thrust, kgf:
take-off mode (H=0, M=0, ISA+15) 7,500
cruising mode
(H=11,000 m, M=0.75, ISA) 1,500
Specific fuel consumption, kg/kgf/h:
take-off mode (H=0, M=0) 0.370
cruising mode (H=11,000 m, M=0.75) 0.608
Bypass ratio 4.98
Pressure ratio (total) 22.17
Gas temperature before the turbine, oK 1,520
Dimensions fan diameter, mm 1,373
Engine dry weight, kg 1,450

D-30KP Turbojet Engine

The D-30KP engine features a two-shaft configuration with exhaust mixing from both ducts. The two-rotor compressor has a three-stage first rotor and an eleven-stage second rotor. The engine has a cannular combustion chamber. The high-pressure turbine has two stages, and the low-pressure turbine has four stages. The nozzle, common for both ducts, has a blade mixer and a mixing chamber. This is Russia’s first production engine to feature cooled rotor blades of the first stage and a clamshell reverser, which does not affect the engine performance at the thrust mode.

Il-76TD Aircraft

Variants D-30KP engine
The D-30KP Series 2 engine provides the design take-off thrust at the ambient air temperature of +30oC. The engine is installed on the Il-76TD, Il-76MD, Il-76TP, Il-78, and A-50 aircraft. The D-30KPV version (without reverser) is developed for the A-40 aircraft.

NK-25 and D-30F6 Turbofan Engine Technology

NK-25 Turbofan Engine Technology

 The NK-25 three-stage bypass turbofan engine features turbine blade radial clearance active control and stator rings perforation for increased compressor stability. The rotor blades
and the nozzle vanes are cooled with vortex
flows. The engine has an anti-surge protection
with automatic recovery of the initial operation mode. The engine control system is electronic.
The NK-25 engine is designed for the Tu-22M3E multirole aircraft.


D-30F6 Turbofan Engine

D-30F6 Turbofan Engine Technology. The D-30F6 engine features a two-shaft configuration with exhaust mixing from both ducts. The engine consists of seven modules. It has a low-pressure five-stage compressor, a high-pressure ten-stage compressor and a cannular combustion chamber. The low- and high-pressure turbines are two-staged. The nozzle vanes and highpressure turbine rotor blades are cooled. The afterburner houses the exhaust mixer and has four ring flame stabilisers. The multivane supersonic nozzle is cooled.

 D-30F6 Turbofan Engine

The engine design enables onboard parameter monitoring. Reliability of the engine is ensured by the protection, backup, and early malfunction detection systems. The electro-hydraulic engine control
system is backed up with the hydraulic system activated if the electronic one has failed to ensure flight safety and effective mission accomplishment.


The engine has unique altitude and airspeed performance, providing maximum airspeed of 3,000 km/h at altitude and 1,500 km/h near ground. The D-30F6 engine is designed to power the MiG-31E fighter/interceptor.

D-30F6 Turbofan Engine Specifications
Thrust, kgf:
max continuous (H=0, M=0, ISA) 9,500
full afterburner 15,500
Specific fuel consumption, kg/kgf/h:
max continuous (H=0, M=0) 0.20
full afterburner 1.90
Bypass ratio 0.57
Air consumption, kg/sec 150
Pressure ratio (total) 21.15
Gas temperature before the turbine, oK 1,640
Engine dry weight, kg 2,416

AL-31F Turbofan Engine Technology

AL-31F Turbofan Engine Technology. The AL-31F engines have modular design, with a four-stage variable low-pressure compressor and a two-shaft turbine. The nine-stage high-pressure compressor has a variable-area first group of stages. The combustor is of an annular type. The single-stage high and lowpressure turbines have active radial clearance control. The air-to-air heat exchanger of the cooling system is placed in the external duct, and is fitted with a device preventing air flow in dry-thrust engine operation mode. 

The afterburner is common for both ducts. The supersonic nozzle has a variable-area design. The engine has a top-mounted gearbox, a looped oil system, and an autonomous startup system. The main control system is electronic, while the auxiliary one is hydraulic. The engine features a surge termination system and high gas-dynamic stability of the compressor.

AL-31F Turbofan Engine

The AL-31F engines are available both in standard and tropicalised variants. They are operational in a wide altitude/airspeed envelope, and provide stable operation in deep air intake surge modes at Mach numbers of up to 2.0, in controlled, inverted and flat spins, and enable execution of aerobatics in the dynamic operation mode at negative airspeeds of up to 200 km/h. The engines boast high gas dynamic stability and durability, enabling their operation in extreme conditions with air intake pressure irregularities and pulsing.

Variants AL-31F Turbofan Engine Technology
- The AL-31F engine is designed for installation in the Su-27, Su-30, Su-32, and Su-35 aircraft.

- The AL-31F Series 3 engine is designed to power the Su-33 aircraft.

- The AL-31FN engine is a development of the AL-31F engine featuring both bottom and top
gearboxes designed for the Chinese J-10A aircraft.

- The AL-31FP engine is another development of the AL-31F engine with a swiveling nozzle for the Su-30MK.

Saturday, July 28, 2012

AL-21F-3 and RD-33 Turbo Jeet

The AL-21F-3 engine features a single-shaft configuration. The 14-stage compressor has a sophisticated control system. The cannular combustion chamber has 12 flame tubes. The three-stage turbine is of an impulse-reaction
type. The blades of the first and second turbine stages are cooled with the bleed air taken fromThe compressor. The afterburner has three annular stabilisers and six fuel manifolds with spray and swirl-type nozzles. A perforated screen is
installed to ensure internal cooling. The fully variable area propelling nozzle consists of the subsonic
convergent and supersonic divergent rims.

AL-21F-3 engine

AL-21F-3 Specifications
Thrust (H=0, M=0, ISA), kgf:
max continuous 7,800
min afterburner 9,700
full afterburner 11,250
Specific fuel consumption, kg/kgf/h:
economy power (H=0, M=0) 0.80
cruising mode 0.76
max continuous 1.86
Air consumption, kg/sec 104
Pressure ratio 14.55
Gas temperature before the turbine, oK 1,385
Dimensions, mm:
length /diameter 5,340/1,030
Engine dry weight, kg 1,800

RD-33 Turbofan Engine

The RD-33 engine has a two-shaft turbine configuration with exhaust mixing in the afterburner. The engine features a modular design. The lowpressure compressor has four stages; the highpressure compressor has nine stages. The engine has a short annular combustion chamber and single-stage low- and high-pressure turbines. The afterburner is common for both ducts. The engine
features a variable-area supersonic propelling nozzle. Due to good gas-dynamic stability, the RD-33 engines do not impose any limitations on piloting and feature high spool-up capacity. The RD-33 is designed to power the MiG-29 fighter family.

RD-33 Turbofan Engine
MiG-29 aircraft

The RD-33 Series 3 engine with an  service life is designed to power MiG-29M, MiG- 29M2, MiG-29K and MiG-29KUB aircraft. The RD-33N engine is designed to power the Mirage F1 fighter upgrade. It has a bottom gearbox, and can also be fitted on MiG-21 and Mirage III aircraft upgrades. The RD-93 engine was developed for the Chinese FC-1 aircraft. The RD-133 engine is designed for the MiG-29 aircraft. It features a fully variable nozzle with thrust vectoring and a new automatic hydromechnical electronic control system.