RD-33

Submitted by :SHIVI SHARMA (A4717209007)

Current production R-25, R-29B, RD-33. RD-33 is a TWIN SPOOL AXIAL FLOW

TURBOFAN ENGINE with low bypass ratio. Provided with thrust augmenter where the

combusted-compressed hot air and the bypass air mixture is obtained and burnt.

Variable area jet nozzle. 8000-9000 kgf thrust is achieveable. Assembled in MIG-29 aircraft as twin engine

and can achieve Mach 2.3.

INTRODUCTION

LPC -4 , HPC -9 Compressor pressure ratio 20-22 Air mass flow (kg/sec) 76+1.5 N1 (100%) -11000 , N2 (100%) -15511 Combustion Chamber Annular HPT-1, LPT-1 TET (Turbine entry temperature) 1250' C

(max) JPT (Jet Pipe Temperature) 875'C (max) Maximum thrust without AB (kgf) 5040 Full AB performance thrust (kgf) 8300 Length (mm) 4106 Maximum Diameter (mm) 1000 Weight (kg) 1217+2% Bypass ratio 0.45

ENGINE SPECIFICATIONS

Low-bypass turbofan engine. High specific thrust. Provide thrust using combination of a fan

and a jet exhaust nozzle. Part of the airstream from the ducted fan

passes through the core, providing oxygen to burn fuel to generate power.

Less exhaust noise. High bypass turbofan engine results in

greater weight.

DESIGN DETAILS

A desired shape is obtained using electrical discharges (sparks).

Anode- work piece, cathode- tool electrode. Decreasing distance b/w 2 electrodes increase

electric field. Brass is at Y- axis. Used for obtaining desired

shape. It has high tensile strength. Distilled water used to flush out carbon

deposited. Insulated properties restored, electric potential

maintained after process.

ELECTRODE DISCHARGE MACHINE(M)

Cont….

ADVANTAGES Complex shapes, hard materials with low

tolerances. No direct contact between tool and work

piece. Therefore delicate sections and weak materials can be machined without any distortion.

A good surface finish can be obtained.

DISADVANTAGES The slow rate of material removal. Time & Cost. Reproducing sharp corners on the work piece

is difficult due to electrode wear. Power consumption is high. "Overcut" is formed. Excessive tool wear.

Used for protection of inner systems from formation of ice

Connected with secondary air bleed from combustion chamber

DOOM For anti icing on the front of the aircraft. Hot gas pipeline is connected from

combustion chamber to doom to melt ice. It transfers about 7Kg of air in 1 second.

ANTI ICING SYSTEM

Total of 49 bearings, out of which only 5 are main – IGV, compressor, combustion chamber, turbines.

Ball & Roller bearings are used.

Ball bearings have less contact area thus reduces friction. They also take care of radial forces.

Roller bearings take care of axial forces acting.

BEARINGS

Amount of exhaust & outlet area is controlled making use of flap arrangement.

4 Heat shields provided to resist high temperature.

Throat is variable from 475mm to 750mm

Increases thrust by decreasing throat.

Total 24 flaps controlled by hydraulic pump which gets power from accessory gearbox.

VARIABLE AREA NOZZLE

Used for 2 RD-33 engines simultaneously, thus reducing drive transmission weight.

Different purposes are : It transmits rotary motion from the turbine

starter to the main engine during start It transmits drive to aircraft accessories from

the turbostarter. It transmits power from the main engines to

various aircraft systems. Power being transferred (h.p.) 2312 Rotation speed at input shaft (rpm) 13443 Mass (kg) 255

AIRCRAFT ACCESSORY GEARBOX (AAG)

Angular drive Oil unit Air separator NP-96 pump Main fuel pump(NR) Afterburner fuel pump(FN) Hydraulic pump Booster pump Afterburner Light up

metering unit: Radiator: Scavenging Pump

DIFFERENT UNITS ON AAG

What all we have learnt about--- Engine operations(Air breathing low by pass

turbofan engine). Manufacturing techniques (Casting, EDM,

cold working etc). Few working systems of/on aircraft. Various instruments used on aircraft (AAG,

pumps etc).

CONCLUSION

THANK YOU