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
8.
9. CONSTRUCTION
pyrotechnic igniter
fuel injector
fuel turbo-pumps
gas turbine-
cryo valves
Regulators
The fuel tanks
rocket engine- nozzle