Cryogenic rocket engines use cryogenic fuels like liquid hydrogen and liquid oxygen that must be stored at extremely low temperatures to remain liquid. They have several advantages like high thrust and specific impulse but also disadvantages like complexity and cost. Common cryogenic engines include the RL-10, CE 7.5, and CE-20 which use liquid hydrogen and liquid oxygen and have specifications like thrust levels and specific impulse. Cryogenic engines require specialized construction elements to handle the extreme cold like fuel injectors, turbo-pumps, valves and tanks.

1. Cryogenic rocket
engine

2. CONTENTS
1. Cryogenic
2. Introduction
3. History of cryogenic
4. Construction
5. Working principle
6. Application
7. Advantage
8. Disadvantage
9. Conclusions

3. CRYOGENIC
Cryogenic is derived from greek , Kryos means cold , genes means
production.
Cryogenic is the study of production and behavior of materials at very
low temperature (Below 150*C ,123*K,-238*F)
 Oxygen liquefies at -183*C
 Hydrogen liquefies at -253*C

4. INTRODUCTION
1. A cryogenic rocket engine is a engine which use cryogenic fuel.
2. Cryogenic fuel are fuel that requires storage at extremely low
temperature in order to maintain the in a liquid state.
3. Various cryogenic fuel-oxidizer combination have been fired but
the combination of liquid hydrogen (LH2), and the liquid oxygen
(LOX) oxidizer is most used.

5. RL-10
 The RL-10 was the first liquid Hydrogen
Cryogenic engine to nr built in the
United States, and development of the
engine by Marshall Space Flight Center
and Pratt & Whitney began in the 1950s,
with the first flight occurring in 1961
 These engines were one of the main
factors of NASA's success in reaching
the Moon by the Saturn V rocket

6. CE 7.5
 The specifications and key characteristics of
the engine are:
 Operating Cycle - Staged combustion
Propellant Combination - LOX / LH2
 Maximum thrust (Vacuum) - 75 KN
 Operating Thrust Range -73.55 kN to 82 kN
 Chamber Pressure (Nom) - 58 bar
 Engine Mixture ratio (Oxidizer/Fuel by mass) -
5.05
 Engine Specific Impulse - 454 ± 3 seconds
(4.452 ± 0.029 km/s)
 Engine Burn Duration (Nom) - 720 seconds
 Propellant Mass - 12800 kg

7. CE-20
The specifications of the engine as listed on the
 Operating Cycle-Gas Generator
 Propellant Combination - LCX/LHE
 Thrust Nominal (Vacuum) - 200 KN
 Operating Thrust Range - 180 KN to 220 KN
(To be set at any fix values)>
 Chamber Pressure (Nom) - 6 Mpa
 Engine Mixture ratio (Oxidizer/Fuel by
weight) -5.05
 Engine Specific Impulse = 443 + 3 seconds
(4.344 ± 0.029 km/s)
 Engine Burn Duration (Nom)-595 seconds
 Total Flow rate-462 kg/s
 Nozzle Area ratio-100
 Mass-588 kg

9. CONSTRUCTION
 pyrotechnic igniter
 fuel injector
 fuel turbo-pumps
 gas turbine-
 cryo valves
 Regulators
 The fuel tanks
 rocket engine- nozzle