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1. SUMMER TRAINING PRESENTATION
ON
ASSEMBLY OF AL31FP ENGINE
SUBMITTED BY – GUIDED BY –
MOHIT KUDAL Mr. NIHAR RANJAN PATRO
ROLL NO – 16/202 (Sr. MANAGER)
AERONAUTICAL ENGINEERING

2. CONTENT
History
Introduction
Section involved
i)Cold Section
• IGV
• Compressor Module
ii)Hot Section
• Combustion Chamber
• Turbine Module
• A/B
• Nozzle
Conclusion
References

3. HISTORY
 HAL is the one of the Asia premier organization of present
Aerospace industry.
 HAL has 20 production Units and 11 Research & Design
Centers in 8 locations in India.
 HAL play a major role in defence sector.
 R&D program developed for both Defense and Civil Aviation
sector.
 HAL was conferred NAVRATNA status by the Government of
India on 22nd June 2007.
 Currently the chairman and managing director of HAL is R
Madhvan.

4. BENGALUR
U
COMPLEX
MIG
COMPLEX
HELICOPTER
COMPLEX
ACCESSORIE
S
COMPLEX
DESIGN
COMPLEX
HAL Corporate
 HAL Nasik and HAL Koraput come under MIG Complex.
HAL Koraput division is manufacturing and overhauling unit
for various aero engines.
 As per the present scenario the division manufactures only
AL31FP engine for SUKHOI- 30MKI aircraft.
 It overhauls
• AL31FP for SUKHOI -30 MKI
• RD33 for MIG-29
• R29B for MIG -27M
• R25 for MIG -21BISON

5. WHAT IS AL31FP ?
 AL 31 FP engine stands for
A-Name of designer- Arkhip Mikhailovich Lyulka
L-Name of company- Lyulka, now NPO Saturn
31-stands for series
F-stands for after burner (Farsa in Russian language)
P-stands for thrust vectoring nozzle (TVC) (Povorothoye
in Russian language)

6. AL31FP ENGINE PARAMETERS
 Dry weight - 1570kg
 Engine Length - 4990mm
 Inlet Diameter - 910mm
 External Diameter - 1280mm
 RPM
• LP ROTOR - 10200rpm
• HP ROTOR - 13300rpm
 Bypass Ratio - 0.57:1
 High Thrust to Weight Ratio – 8:1
 Max. air mass flow - 112kg/s
 Total Compression Ratio – 23:1

7. INTRODUCTION TO AL31FP ENGINE

9. PARTS OF AL31FP ENGINE
1. IGV
2. LP MODULE
3. INTERMEDIATE CASING
4. HP MODULE
5. COMBUSTION CHAMBER
6. HPTR MODULE
7. LPTR MODULE
8. A/B (REHEAT)
9. EXHAUST

10. COLD SECTION
• Casing attached with LPC module is the variable
IGV
• Blades of IGV are of dual support
• Purpose of the IGV is to direct the air into the 1st
stage of the compressor
• Angle changed by hydraulic actuator
• Angle of rotation is from min. of 0 to max. of 30
degree
• Changing the air mass flow
 IGV

11. INLET GUIDE VANE

12. COMPRESSOR MODULE
 A compressor is a mechanical device that increases
the pressure of a gas by reducing its volume
 Axial type
 Dual Casing
 Parts
1. LPCR(4 stage)
2. HPCR(9 stage)
3. Intermediate Casing
4. LPCS(4 stage)
5. HPCS(9 stage)
 Rotating blades-981  Stator blades-1462

13. LPCR
 4 stage compressor
 Disc-dram is electron beam welded structures
 1st ,2nd & 3rd stages are drum type
 4th stage is disc type

14. INTERMIDIATE CASING
 It is load bearing element of engine
 Intermediate casing, the air coming out from LPC
is divided into two stream
 The following are installed in the intermediate
casing:
 Rear support of LPC
 Front support of HPC
 CBD drive

15. HPC ROTOR
 It is drum-disc construction of 9 stage compressor
 1st- 6th stage Discs are electron beam welded
7th -9th stage Disc are joined to shaft with 24 tie bolts
 Rotor is dynamically balanced to 25gm-cm

16. HPCR

17. HOT SECTION

18. MAIN COMBUSTION CHAMBER
 Internal combustion engine in which expanding gases from
the combustion chamber drive the blades of a turbine.
 Annular type combustor.
 main components of combustion chamber:-
 Spark Plug
 Flame Tube
 Diffuser
 Manifold
 CCIC
 CCOC

19. TURBINE
 The high pressure and temperature gas expands thus driving
the turbine
 turbine module comprises of:
 HPTR Module
 LPTR Module
 Turbine Support
 Turbine Cooling

20.  It consists of 1st stage NGV, Disc and a HPT Shaft
 Numbers of blade :- 90
 It is connected to the HPCR shaft with the help of 24 drift
bolts
 HPTR blades are mono cast and hollow cast
 Investment casting to increase creep resistance
 It’s blade having larger thickness
 It’s blade having curvature compared to that of compressor
blades
 HPT shaft transmits power to the HPCR
HPTR MODULE

21. LPTR MODULE
It consists of 2nd stage NGV, Disc and a LPT Shaft.
 Numbers of blade :- 90
 The LPT shaft is made of 3 piece shaft.
 It is coupled with a disc by 36 radial pins.
 LPTR blades are mono cast and hollow cast.
 Investment casting to increase creep resistance.
 It’s blade having larger thickness and dual support type.
 It’s blade having curvature compared to that of compressor
blades.
 LPT shaft transmits power to the LPCR.

22. A/B COMBUSTION CHAMBER (REHEAT
CHAMBER)
 It’s come after the mixture.
 5 fuel manifold installed .
 Manifold provide fuel during the reheat process.
 Increase the pressure and temperature.
 Producing extra thrust.
 Uses
 Take-off
 Climb
 Combat

23. VARIABLE JET NOZZLE (TVC)
 It is an axi-symmetric vectoring nozzle.
 Thrust vector angle is14º±1.
 Thrust generated is 12,500kgs in reheat mode.
 TVC casing are made up of Ti-alloy.
 TVC inner flaps are made of Ni-alloy.
 20 hydraulic cylinders used
 16 cylinders control Throat area.
 4 cylinders control Vectoring
 16 pneumatic cylinders control exit diameter of
TVC.

24. CONCLUSION
 This internship project helped us a lot to understand about various
components of turbofan jet engines, and their assembly, manufacturing and
testing of engine.
 We have got a virtual experience over the components, their purpose,
functioning and design.

25. REFERENCES
 Project report
 Ganesan, V., 2010. Gas Turbines 3E. Tata McGraw-Hill Education.
 https://hal-
india.co.in/Product_Details.aspx?Mkey=54&lKey=&CKey=31
 https://www.grc.nasa.gov/www/k-12/UEET/StudentSite/engines.html

26. THANK YOU