Pure liquid oxygen as oxidizer operates significantly at hotter combustion chambers due to which extremely high heat fluxes are produced which is not available in any jet engines. In jet engines petrol, diesel, kerosene, gasoline, LPG, CNG and PNG, etc., are used having the properties of hydrocarbons.
The basic construction and working of the engine could be explained as follows:
Gas Generator: The main function of the gas generator is the delivery of sufficient amount of driver gas at designed temperature and pressure which generates continuous propellant supply to thrust chamber.
Turbo Pumps: They receive liquid propellants at low pressure from vehicle tanks which are then supplied to the combustion chamber. Generally, radial and axial turbines are used.
Pump: In simple words, pump adds energy to propellants through the rotation. The material used for all the turbo machinery chambers are Al alloys, H.S.S, S.S, and NiTi-Co based alloys.
Thrust Chamber: Thrust is generated in thrust chamber by the efficiency conversion of Chemical energy into gases kinetic energy This can be obtained by combustion of liquid propellants. In the combustion chamber followed by the acceleration of hot gases throw conversion/diversion section of the nozzle to acquire high gas velocities and hands thrust.
Nozzle: The pressure generated in the combustion chamber can be used increase thrust by acceleration of combustion gas to high supersonic velocity. Nozzle generally passes parabolic enters. (Because when high velocities gases entrance and at exit of nozzle, pressure of exhaust gas increases with high value and hence velocity and hence velocities reduces).
Indian Cryogenic Engine:
GSLV-D5 is the eighth flight of India’s Geosynchronous Satellite Launch Vehicle (GSLV). It is also the fourth developmental flight of GSLV. During this flight, the indigenously developed Cryogenic Upper Stage (CUS) will be flight tested for the second time GSLV is a three-stage launch vehicle with solid, liquid and cryogenic stages. It is designed to inject 2 Tonne class of communication satellites to Geosynchronous Transfer Orbit (GTO). The four liquid L40 strap-ons, as well as the second stage of GSLV, use storable liquid propellants. The GSLV-D5 vehicle is configured with its
first and second stages similar to the ones flown during earlier GSLV missions. The third stage is the indigenous cryogenic stage. The metallic payload fairing with a diameter of 3.4 meters is adopted for GSLV-D5. S-band telemetry and C-band transponders enable GSLV-D5 performance monitoring, tracking, range safety/flight safety and Preliminary Orbit Determination (POD).
Indigenous Cryogenic Upper Stage
A Cryogenic rocket stage is more efficient and provides more thrust for every kilogram of propellant it burns compared to solid and earth-storable liquid propellant rocket stages. Specific impulse (a measure of the efficiency) achievable with cryogenic propellants (liquid Hydrogen and liquid Oxygen) is much higher compared to earth storable liquid and solid propellants, giving it a substantial payload advantage.
References: www.wikipedia.org; https://www.rroij.com/open-access/an-experimental-study-of-cryogenic-engine.pdf; https://www.nasa.gov; http://www.isro.gov.in