The document discusses cryogenic engines, focusing on their components, design, and operational procedures, including advantages and disadvantages. It highlights the history of cryogenic engine development, with the first successful launch involving human spaceflight in 1987. The conclusion emphasizes the efficiency of cryogenic engines over traditional propulsion systems.

1. CRYOGENIC ENGINE
the coolest hot engine
by
VOLETI AJAY KUMAR
THOTA VISWA CHAITANYA

2. CONTEXT
 What is cryogenic engine
 Law of action-reaction
 Components of cryogenic engine
 Design of cryogenic engine
 Engine start and cut-off
 Advantages & disadvantages cryogenic engine
 Conclusion

3. INTRODUCTION & HISTORY
 Cryogenics is the study of production of very
low temperature nearly about ‘123K’ in which
the material’s behavior and properties are
studied.
 In 1963, United States of America was the first
country to develop the CRE.
 In 1987, first CRE was launched with human
in space.

4. Law of action-reaction

5. Main Components
 Turbo pump
 Gas turbine
 Combustion chamber
 Nozzle

6. Turbo pump

7. Gas turbine
 It is also called combustion turbine.
 Its main purpose is to supply power
to the compressor and turbo pump.

8. Combustion chamber
 Combustion chamber is the place
where the combustion of
propellants will takes place.
 The dimensions of the cylinder are
such that the propellant is able to
combust thoroughly.

9. Nozzle

10. CROGENIC ENGINE
THE COOLEST HOTENGINE

11. Engine design
To introduce propellant into the
combustion chamber, two principle
designs of LRE is used :
 Pressure-fed design
 Pump-fed design

12. Pressure-fed design
 In a pressure fed design, the
propellants are forced to the
combustion chamber by a pressure
gas which pressurises the tank.

13. Pump fed design
 In pressure fed design, the
propellant is forced to the
combustion chamber with the help
of a pump.
STAGED CYCLE:

14. Full Flow Staged Cycle Expander cycle

15. Working of engine
 TO START A LRE:
The following operations should be
performed:
a. Pressurizing the tank or vaporising
propellants
b. Starting of turbine ( if turbo pump is
applied)
c. Opening of main vents
d. Combustion ( with the pyrotechnic
initiator )

16.  ENGINE CUT-OFF :
Large engines can not be cut off only by
closing the main propellant valve.
It can be achieved by
 Redirecting it into a low pressure line
followed by closing the propellant valve.
 The pressure feed engines can be cut off by
propellant depletion.
 If the engine is pump feed, first the
propellant flow to the gas generator is
lowered.

17. Advantages
 Eco-friendly
 Non-toxic
 Non-corrosive
 Safer to handle & store
 High specific impulse
Disadvantages
 Low temperature
propellants – Complex to
store
 Need for ignition system
 Highly relative gases
 Leakage

18. ENGINE DESCRIPTION VIDEO

19. GSLV-D5 stages

20. Conclusion
 All the present programs are related to the
Cryogenic upper stages of launching vehicles.
 It is more efficient over conventional engines.

21. Any queries ???

22. THANK YOU