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Cryogenic Rocket Engine

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Discovery Saturn V GSLV MkIII

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Introduction

A cryogenic rocket engine is a rocket engine that usesa cryogenic fuel or oxidizer, that is, its fuel or oxidizer aregasses liquefied and stored at very low temperatures.

Rocket engines need high mass flow rate of both oxidizerand fuel to generate a sufficient thrust.

The liquid oxygen oxidizer and liquid hydrogen fuelcombination is one of the most widely used.

The Fuel and Oxidizer are cooled to cryogenic temperaturesto liquefy the gases and reduce the size of the fuel tanks

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4/28/12 Brief history

Rocket Engines were developedduring the space race between theUSA and the then Soviet Union

The first rockets used Solidpropellants for their firing

Later, It was realized that the otherpropellants could give far morespecific impulse than solids

This lead to the invention of thefirst Cryogenic Liquid propelledrocket engine the RL10

It was developed by Pratt &Whitneys Rocketdyne for the Apollomoon mission.

This was how the first cryogenicrocket engine was born.

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Cryogenic rocket EngineFundamentals

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4/28/12 Working of Cryogenic Propellants

Special insulated containers and vents are used to preventgas from the evaporating liquids to escape.

The liquid fuel and oxidizer are fed from the storage tank toan expansion chamber.

Then it is injected into the combustion chamber.

In this chamber, they are mixed and ignited by a flame or spark.

The fuel expands as it burns and the hot exhaust gases are

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4/28/12 Cryogenic propellant

In a cryogenic propellant the fuel and the oxidizer are in the form of very cold, liquefied gases.

Super cooled gases used as liquid fuels are called cryogenic fuelsas they stay in liquid form even though they are at a temperaturelower than the freezing point.

To store these propellants aboard a rocket is a very difficult task asthey have very low densities.

Thus by cooling and compressing them into liquids, we can vastlyincrease their density and make it possible to store them in largequantities in smaller tanks.

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4/28/12 Construction

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construction

The major components of a cryogenic rocket engine are:

the thrust chamber or combustion chamber

pyrotechnic igniter

fuel injector

fuel turbo-pumps

gas turbine

cryo valves Regulators

the fuel tanks

rocket engine nozzle

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4/28/12 Cryogenic Engine Working

Cryogenic cycles usually work in one the four following cycles:1. Expander Cycle

2. Gas Generator Cycle

3. Pressure fed Cycle

4. Staged Combustion Cycle

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4/28/12 Expander Rocket Cycle

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4/28/12 Gas Generator Rocket Cycle

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4/28/12 Pressure fed Rocket Cycle

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Staged Combustion RocketCycle

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4/28/12 Cryogenic Propellants

Liquid oxygen and liquid hydrogen are used as the propellantin the high efficiency main engines of the Space Shuttle.

Another cryogenic fuel with desirable properties for spacepropulsion systems is liquid methane (-162 C). When

burned with liquid oxygen, methane is higher performing thanstate-of-the-art storable propellants but without the volumeincrease common with LOX/LH2 systems, which results in anoverall lower vehicle mass.

LOX/methane is also clean burning and non-toxic. Future

missions to Mars will likely use methane fuel because it canbe manufactured partly from Martian in-situ resources.

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4/28/12 Advantages

High Energy output per unit mass

Hydrogen has the highest calorific value when among allthe fuels used for combustion

Economical

Use of oxygen and hydrogen as fuels is very economical, asliquid oxygen costs less than petrol.

Highest specific impulse

This type of rocket engine gives the highest specificimpulse that can be achieved

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4/28/12 Disadvantages

Boil off Rate

Highly reactive gases

Leakage

Hydrogen Embrittlement

Zero Gravity conditions

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4/28/12 The RL-10 of Saturn I

This was the first cryogenic rocket engine made by the USAfor its Saturn I rocket

Thrust = 66.7 kN

Specific impusle = 4.25 kN.s/kg

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4/28/12 The Vulcain of Ariane 5

This engine is used to power the ariane rockets made by the

European Space Agency It is similar in power to the main engine of the spaceships

made by USA

Thrust 1120kN

Specific impulse 433 s

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4/28/12 CE 20 of GSLV III

This is the first cryogenic engine being developed by India

It might be used to power the GSLV III

Thrust = 200 kN

Specific Impulse = 444 s

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Why didn't the cryogenic engine of India ignite?

The GSLV D3, which lifted off well from Sriharikotaon Thursday, April 15, 2010 later plunged into thesea as the indigenous cryogenic engine failed to

ignite.

There had been some problem developed in one of the turbopumps that supply fuel to the cryogenicengine.

The vehicle developed problems when thecryogenic upper stage should have ignited 304seconds after the lift-off, and it fell into the sea

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