I need paper presentation on cryogenic engine

A cryogenic rocket stage is more efficient and provides more thrust for every kilogram of burning propellant compared to solid and storable liquid propellant rocket stages on the ground. The specific thrust (a measure of efficiency) attainable with cryogenic propellants (liquid hydrogen and liquid oxygen) is much higher compared to liquid and solid propellants stored on the ground, giving it a substantial payload advantage.

However, the cryogenic stage is technically a very complex system compared to solid or liquid propellant storable stages in the ground due to its use of propellants at extremely low temperatures and the associated thermal and structural problems.
Oxygen is liquefied at -183 degrees C and hydrogen at -253 degrees C. Propellers at these low temperatures are pumped using turbo pumps operating at about 40,000 rpm. It also involves complex ground support systems such as propellant storage and filling systems, cryo-engine testing facilities, and scenario testing facilities, transport and handling of cryo fluids and related safety aspects.

The ISRO High-Stage Cryogenic Project (CUSP) provides for the design and development of the cryogenic upper stage to replace the stage acquired from Russia and used on GSLV flights. The main engine and two smaller engines of the CUS steering together develop a nominal thrust of 73.55 kN in vacuum. During the flight, CUS is fired for a nominal time of 720 seconds.