This document provides an overview of cryogenic rocket engines. It discusses that cryogenic fuels require storage at extremely low temperatures to remain liquid, and the most widely used combination is liquid hydrogen and liquid oxygen. The major components of cryogenic rocket engines are described, including the combustion chamber, injectors, pumps, valves and tanks. Advantages are high energy density and clean, non-toxic exhaust, while challenges include difficulties storing cryogenic liquids for long periods. Common applications are in rockets utilizing these high-performance fuels.

1. CRYOGENIC
ROCKET ENGINE

2. CONTENTS
1.CRYOGENICS ?
2.INTRODUCTION
3.HISTORY OF CRE
4.CONSTRUCTION
5.WORKING
6.APPLICATIONS
7.REFERENCES

3. CRYOGENICS
 The word ‘cryogenics’ is derived from Greek,
meaning “production of freezing cold”.
 cryogenics is the study of the production and
behaviour of materials at very
low temperatures (below −150 °C, −238 °F or 123 K).
 Rather than the relative temperature scales of
Celsius and Fahrenheit, cryogenicists use the
absolute temperature scales. These are Kelvin (SI
units) or Rankine scale (Imperial and US units).
 Oxygen liquifies at -183c(90k)
 Hydrogen liquifies at -253c(20k)

4. INTRODUCTION
 A cryogenic engine is a rocket engine that uses
a cryogenic fuel .
 Cryogenic fuels are fuels that require storage at
extremely low temperatures in order to maintain
them in a liquid state.
 Various cryogenic fuel-oxidizer combinations have
been tried, but the combination of liquid hydrogen
(LH2) fuel and the liquid oxygen (LOX) oxidizer is
one of the most widely used.

6. PRINCIPLE
 The basic principle driving a rocket engine are:
 Newton third law of motion
 Law of conservation of momentum
 In principle, cryogenic rocket engine derives thrust
like all other rocket engines by accelerating an
impulse carrier to high speeds.
 The chemical energy stored in the fuel is converted
into kinetic energy by burning the fuel in the thrust
chamber and subsequent expansion in the nozzle to
produce thrust

7. HISTORY
o American and Soviet engineers independently, all discovered
that rocket engines need high mass flow rate of both oxidizer
and fuel to generate a sufficient thrust.
o At that time oxygen and low molecular weight hydrocarbons
were used as oxidizer and fuel pair. At room temperature and
pressure, both are in gaseous state. Hypothetically, if
propellants had been stored as pressurized gases, the size and
mass of fuel tanks themselves would severely decrease rocket
efficiency.
o Therefore, to get the required mass flow rate, the only option
was to cool the propellants down to cryogenic temperatures
(below −150 °C, −238 °F), converting them to liquid form.
Hence, all cryogenic rocket engines are also, by definition,
either liquid-propellant rocket engines or hybrid rocket engines

8.  The RL10 was the first
liquid hydrogen
cryogenic rocket engine
to be 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

9. LPSC MAHENDRAGIRI
 On 1 February 2014, this unit was renamed as Indian
Space Research Organisation (ISRO) Propulsion
Complex and was also made an autonomous
department under ISRO. The main activities carried
out at here are:
 Assembly and integration of liquid engines and
stages
 Testing of liquid engines and stages
 High altitude test facilities for upper stage engines
 Propellant storage facilities

11. C E 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 (as demonstrated during
GSLV Mk2 D5 flight) – 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
Two independent regulators: thrust control and
mixture ratio control
Steering during thrust: provided by two gimbaled
steering engines

12. C E 20
The specifications of the engine as
listed on the LPSC handouts:
Operating Cycle - Gas Generator
Propellant Combination - LOX / LH2
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

13. CONSTRUCTION
The major components of a cryogenic rocket engine are:
1.The combustion chamber (thrust chamber)
2. Pyrotechnic initiator
3.Fuel injector
4.Fuel cryopumps,
5.oxidizer cryopumps
6.Gas turbine
7. cryo valves,
8.regulators,
9.The fuel tanks, and
10. rocket engine nozzle.

16. PRESSURE FED SYSTEM PUMP FED SYSTEM

19. ADVANTAGES
 High Energy per unit mass:
Propellants like oxygen and hydrogen in liquid form give
very high amounts of energy per unit mass due to which the
amount of fuel to be carried aboard the rockets decreases.
 Clean Fuels
Hydrogen and oxygen are extremely clean fuels. When
they combine, they give out only water. This water is thrown out
of the nozzle in form of very hot vapour. Thus the rocket is
nothing but a high burning steam engine
 Economical
Use of oxygen and hydrogen as fuels is very economical, as
liquid oxygen costs less than gasoline.

20. COMPARISON
Solid -fuel
advantages
Solid -fuel
disadvantages
Liquid-fuel
advantages
Liquid-fuel
disadvantages
Very stable,
durable
Can’t be turned off.
Once the burn starts ,
it goes on until the fuel
is used up.
Variable thrust-
The amount of fuel
and rate of burn can
be changed in flight
Fragile, more
complex parts
Fuel system is
simpler, safer and
cheaper
Low efficiency Relatively high
efficiency
Highly complex
system and
requires high
maintenance
More thrust for a
similar rocket size
Fuel decomposes,
must be replaced
Liquid-fuel boosters
are more easily re-
useable.
Oxidizer(liquid
oxygen) must be
kept extremely cold

21. DISADVANTAGES
 Cryogenic liquids difficult to store for longer periods
 High density requires larger tanks
 Highly reactive gases
 Leakage problems
 Boil off rate
 Hydrogen embrittlement
 Zero gravity conditions

22. APPLICATIONS OF CRYOGENICS
 Cryogenic fuels
 Liquid nitrogen: used in cryo-therapy, as a coolant, cryonic
preservation
 Nuclear magnetic resonance spectroscopy: NMR is one of the
most common methods to determine the physical and chemical
properties of atoms by detecting the radio frequency absorbed
and subsequent relaxation of nuclei in a magnetic field.
 Frozen food: Cryogenic gases are used in transportation of
large masses of frozen food.
 Blood banking: Certain rare blood groups are stored at low
temperatures, such as −165 °C.
And many more…..

23. INDIAs ROAD TO
CRE

25. An Indian-made cryogenically-powered rocket,
launch vehicle GSLV-D5, carrying a GSAT-14
satellite, blasts off from the Satish Dhawan Space
Centre at Sriharikota, some 110 kilometers (69
miles) north east of Chennai on January 5, 2014
(AFP Photo / STR)

27. REFERENCES
http://en.wikipedia.org/wiki/solar tree
http://articles.economictimes.indiatimes.com/
http://en.wikipedia.org/wiki/solar energy
http://books.google.co.in/books?id=wm6uAIiuCc8C&
http://en.wikipedia.org/wiki/renewablesenergies
http://library.thinkquest.org/
http://isro.org/
http://howstuffworks.com/