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ISRO's High Thrust Cryogenic Booster Stage (CE20) Development: An Analysis

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ISRO's High Thrust Cryogenic Booster Stage (CE20) Development

Indian_Cryogenic_Stage_Main.jpg

ISRO's CE-20 Cryogenic Booster Stage


What is Cryogenic Engine Technology?
MOST rocket propulsion is achieved through chemical propellants, where chemical energy is converted into the kinetic energy of hot gases that are expelled from the combustion chamber. A propellant is composed of two parts, a fuel that burns and an oxidizer that aids its burning. The chemical energy is first converted into heat energy through combustion. Because of the heat energy that is released, the gaseous products of the combustion expand. As the hot gases escape through the flared-up geometry of the nozzle at the aft end of the combustion chamber, they gain kinetic energy and exit at a very high velocity. The greater the chemical energy content of the propellant, the higher the exit velocity of the hot gases and the resulting thrust.

Note the complex technology that goes into the indigenous Cryogenic Rocket Engine Technology

Rocket propellants come in solid, liquid and gaseous forms. As compared to solid and liquid propellants, gaseous propellants have to be compressed to very high pressures or cooled to very low temperatures in order to achieve a high density. Propellants that are usually gases at room temperature but become liquids when cooled to very low temperatures to achieve the high density are called cryogenic liquid propellants.

ISRO'S CRYOGENIC Upper Stage

ISRO is developing a high thrust cryogenic engine to be used for the upper stage of its heavy lift launch vehicle GSLV Mk-III. This high thrust cryogenic engine produces a nominal thrust of 196.5 kN in vacuum with a specific impulse of 434 seconds. The engine works on “Gas Generator Cycle” which has flexibility for independent development of each sub-system before the integrated engine test, thus minimizing uncertainty in the final developmental phase and reducing development time. This engine generates nearly 2 MW power as compared to 1 MW generated by the engine of Cryogenic Upper Stage (CUS) engine of GSLV. The high thrust cryogenic engine is one of the most powerful cryogenic engines of upper stages in the world.

Weighing 630 tonnes, the GSLV-Mk III is a new-generation launch vehicle. It is 43.43 metres long. Its core liquid stage, called L110, uses 110 tonnes of liquid propellants. The L110 is India's first cluster engine stage containing a cluster of 2 Vikas engines. Clinging on to the core stage are two strap-on, solid propellant booster motors, named S-200, each guzzling up 200 tonnes of solid propellants. They are the biggest solid motors built by ISRO.

The High Thrust cryogenic rocket engine generating a nominal thrust of 19 tonnes was successfully endurance hot tested for a duration of 800 seconds on July 16, 2015 at ISRO Propulsion Complex, Mahendragiri. This duration is approximately 25% more than the engine burn duration in flight. The engine will be used for powering the Cryogenic stage (C25), the upper stage of the next generation GSLV Mk-III launch vehicle of ISRO, capable of launching four tonne class satellites.

Cryogenics is the science and technology of temperatures below 120 Kelvin (−153° Celsius), the limit being defined by the boiling point of methane, a principal component of natural gas. Thus, all cryogenic rocket engines are liquid engines but they should be distinguished from rocket engines that use earth-storable liquid propellants that are liquids at ordinary temperatures and can, therefore, be stored as liquids easily. The most common cryogenic propellants used in rocket engines are liquid hydrogen (LH2), which liquefies at −253° C, as the fuel and liquid oxygen (LOX), which liquefies at −183° C, as the oxidizer.

Cryogenic propellants are preferred as rocket propellants when rockets have to carry payloads of high mass because they have the greatest efficiency in terms of thrust generated. This efficiency is measured by what is called “specific impulse”. It is defined as the thrust generated per unit mass of propellant consumed per unit time or, equivalently, the rate of mass ejected from the rocket nozzle. It is measured in units of seconds.

ISRO has achieved a major milestone by successfully conducting the ground test of Indigenous High Thrust Cryogenic Engine at ISRO Propulsion Complex at Mahendragiri on April 28, 2015 at 1657 Hrs for a duration of 635 seconds. All the propulsion parameters during the tests were found satisfactory and closely matched with predictions. This ground test was preceded in the last few weeks, by four short duration tests of 5.5, 7.5, 20 and 30 seconds.

The Soviet/Russian RD-170 is among the most Powerful Rocket Engines in the World

The high thrust cryogenic engine is designed and realized by Liquid Propulsion Systems Centre (LPSC) at Valiamala with the support of Vikram Sarabhai Space Centre (VSSC) at Thiruvananthapuram. The engine assembly, integration and testing is carried out by ISRO Propulsion Complex (IPRC) at Mahendragiri. Indian Industries have significantly contributed in the realization of the cryogenic engine.

While ground tests conducted so far validate this the design adequacy and performance of the integrated engine, further demonstration tests are planned at engine and stage level to characterize the different performance parameters under various operating conditions. After completion of the tests, the indigenous high thrust cryogenic engine and stage are planned to be flight tested in GSLV Mk- III-D1 mission.
(Disclaimer:Text adapted from ISRO & other Internet Sources, please feel free to correct any mistakes)

@nair @Major Shaitan Singh @Chanakya's_Chant @MilSpec @SpArK @PARIKRAMA @The_Sidewinder @Hindustani78 @acetophenol @Abingdonboy @SarthakGanguly @Dillinger and others (Apology for not able to tag all interested members ).
 
ISRO's High Thrust Cryogenic Booster Stage (CE20) Development

Indian_Cryogenic_Stage_Main.jpg

ISRO's CE-20 Cryogenic Booster Stage


What is Cryogenic Engine Technology?
MOST rocket propulsion is achieved through chemical propellants, where chemical energy is converted into the kinetic energy of hot gases that are expelled from the combustion chamber. A propellant is composed of two parts, a fuel that burns and an oxidizer that aids its burning. The chemical energy is first converted into heat energy through combustion. Because of the heat energy that is released, the gaseous products of the combustion expand. As the hot gases escape through the flared-up geometry of the nozzle at the aft end of the combustion chamber, they gain kinetic energy and exit at a very high velocity. The greater the chemical energy content of the propellant, the higher the exit velocity of the hot gases and the resulting thrust.

Note the complex technology that goes into the indigenous Cryogenic Rocket Engine Technology

Rocket propellants come in solid, liquid and gaseous forms. As compared to solid and liquid propellants, gaseous propellants have to be compressed to very high pressures or cooled to very low temperatures in order to achieve a high density. Propellants that are usually gases at room temperature but become liquids when cooled to very low temperatures to achieve the high density are called cryogenic liquid propellants.

ISRO'S CRYOGENIC Upper Stage

ISRO is developing a high thrust cryogenic engine to be used for the upper stage of its heavy lift launch vehicle GSLV Mk-III. This high thrust cryogenic engine produces a nominal thrust of 196.5 kN in vacuum with a specific impulse of 434 seconds. The engine works on “Gas Generator Cycle” which has flexibility for independent development of each sub-system before the integrated engine test, thus minimizing uncertainty in the final developmental phase and reducing development time. This engine generates nearly 2 MW power as compared to 1 MW generated by the engine of Cryogenic Upper Stage (CUS) engine of GSLV. The high thrust cryogenic engine is one of the most powerful cryogenic engines of upper stages in the world.

Weighing 630 tonnes, the GSLV-Mk III is a new-generation launch vehicle. It is 43.43 metres long. Its core liquid stage, called L110, uses 110 tonnes of liquid propellants. The L110 is India's first cluster engine stage containing a cluster of 2 Vikas engines. Clinging on to the core stage are two strap-on, solid propellant booster motors, named S-200, each guzzling up 200 tonnes of solid propellants. They are the biggest solid motors built by ISRO.

The High Thrust cryogenic rocket engine generating a nominal thrust of 19 tonnes was successfully endurance hot tested for a duration of 800 seconds on July 16, 2015 at ISRO Propulsion Complex, Mahendragiri. This duration is approximately 25% more than the engine burn duration in flight. The engine will be used for powering the Cryogenic stage (C25), the upper stage of the next generation GSLV Mk-III launch vehicle of ISRO, capable of launching four tonne class satellites.

Cryogenics is the science and technology of temperatures below 120 Kelvin (−153° Celsius), the limit being defined by the boiling point of methane, a principal component of natural gas. Thus, all cryogenic rocket engines are liquid engines but they should be distinguished from rocket engines that use earth-storable liquid propellants that are liquids at ordinary temperatures and can, therefore, be stored as liquids easily. The most common cryogenic propellants used in rocket engines are liquid hydrogen (LH2), which liquefies at −253° C, as the fuel and liquid oxygen (LOX), which liquefies at −183° C, as the oxidizer.

Cryogenic propellants are preferred as rocket propellants when rockets have to carry payloads of high mass because they have the greatest efficiency in terms of thrust generated. This efficiency is measured by what is called “specific impulse”. It is defined as the thrust generated per unit mass of propellant consumed per unit time or, equivalently, the rate of mass ejected from the rocket nozzle. It is measured in units of seconds.

ISRO has achieved a major milestone by successfully conducting the ground test of Indigenous High Thrust Cryogenic Engine at ISRO Propulsion Complex at Mahendragiri on April 28, 2015 at 1657 Hrs for a duration of 635 seconds. All the propulsion parameters during the tests were found satisfactory and closely matched with predictions. This ground test was preceded in the last few weeks, by four short duration tests of 5.5, 7.5, 20 and 30 seconds.

The Soviet/Russian RD-170 is among the most Powerful Rocket Engines in the World

The high thrust cryogenic engine is designed and realized by Liquid Propulsion Systems Centre (LPSC) at Valiamala with the support of Vikram Sarabhai Space Centre (VSSC) at Thiruvananthapuram. The engine assembly, integration and testing is carried out by ISRO Propulsion Complex (IPRC) at Mahendragiri. Indian Industries have significantly contributed in the realization of the cryogenic engine.

While ground tests conducted so far validate this the design adequacy and performance of the integrated engine, further demonstration tests are planned at engine and stage level to characterize the different performance parameters under various operating conditions. After completion of the tests, the indigenous high thrust cryogenic engine and stage are planned to be flight tested in GSLV Mk- III-D1 mission.
(Disclaimer:Text adapted from ISRO & other Internet Sources, please feel free to correct any mistakes)

@nair @Major Shaitan Singh @Chanakya's_Chant @MilSpec @SpArK @PARIKRAMA @The_Sidewinder @Hindustani78 @acetophenol @Abingdonboy @SarthakGanguly @Dillinger and others (Apology for not able to tag all interested members ).

IMG_0027.JPG

Cryogenic Engines already operational - CE-7.5 -

rocketliquid-20-638.jpg

Other Cryogenic Engines Under Development -

I9zz7m1.jpg
 
ISRO's High Thrust Cryogenic Booster Stage (CE20) Development

Indian_Cryogenic_Stage_Main.jpg

ISRO's CE-20 Cryogenic Booster Stage


What is Cryogenic Engine Technology?
MOST rocket propulsion is achieved through chemical propellants, where chemical energy is converted into the kinetic energy of hot gases that are expelled from the combustion chamber. A propellant is composed of two parts, a fuel that burns and an oxidizer that aids its burning. The chemical energy is first converted into heat energy through combustion. Because of the heat energy that is released, the gaseous products of the combustion expand. As the hot gases escape through the flared-up geometry of the nozzle at the aft end of the combustion chamber, they gain kinetic energy and exit at a very high velocity. The greater the chemical energy content of the propellant, the higher the exit velocity of the hot gases and the resulting thrust.

Note the complex technology that goes into the indigenous Cryogenic Rocket Engine Technology

Rocket propellants come in solid, liquid and gaseous forms. As compared to solid and liquid propellants, gaseous propellants have to be compressed to very high pressures or cooled to very low temperatures in order to achieve a high density. Propellants that are usually gases at room temperature but become liquids when cooled to very low temperatures to achieve the high density are called cryogenic liquid propellants.

ISRO'S CRYOGENIC Upper Stage

ISRO is developing a high thrust cryogenic engine to be used for the upper stage of its heavy lift launch vehicle GSLV Mk-III. This high thrust cryogenic engine produces a nominal thrust of 196.5 kN in vacuum with a specific impulse of 434 seconds. The engine works on “Gas Generator Cycle” which has flexibility for independent development of each sub-system before the integrated engine test, thus minimizing uncertainty in the final developmental phase and reducing development time. This engine generates nearly 2 MW power as compared to 1 MW generated by the engine of Cryogenic Upper Stage (CUS) engine of GSLV. The high thrust cryogenic engine is one of the most powerful cryogenic engines of upper stages in the world.

Weighing 630 tonnes, the GSLV-Mk III is a new-generation launch vehicle. It is 43.43 metres long. Its core liquid stage, called L110, uses 110 tonnes of liquid propellants. The L110 is India's first cluster engine stage containing a cluster of 2 Vikas engines. Clinging on to the core stage are two strap-on, solid propellant booster motors, named S-200, each guzzling up 200 tonnes of solid propellants. They are the biggest solid motors built by ISRO.

The High Thrust cryogenic rocket engine generating a nominal thrust of 19 tonnes was successfully endurance hot tested for a duration of 800 seconds on July 16, 2015 at ISRO Propulsion Complex, Mahendragiri. This duration is approximately 25% more than the engine burn duration in flight. The engine will be used for powering the Cryogenic stage (C25), the upper stage of the next generation GSLV Mk-III launch vehicle of ISRO, capable of launching four tonne class satellites.

Cryogenics is the science and technology of temperatures below 120 Kelvin (−153° Celsius), the limit being defined by the boiling point of methane, a principal component of natural gas. Thus, all cryogenic rocket engines are liquid engines but they should be distinguished from rocket engines that use earth-storable liquid propellants that are liquids at ordinary temperatures and can, therefore, be stored as liquids easily. The most common cryogenic propellants used in rocket engines are liquid hydrogen (LH2), which liquefies at −253° C, as the fuel and liquid oxygen (LOX), which liquefies at −183° C, as the oxidizer.

Cryogenic propellants are preferred as rocket propellants when rockets have to carry payloads of high mass because they have the greatest efficiency in terms of thrust generated. This efficiency is measured by what is called “specific impulse”. It is defined as the thrust generated per unit mass of propellant consumed per unit time or, equivalently, the rate of mass ejected from the rocket nozzle. It is measured in units of seconds.

ISRO has achieved a major milestone by successfully conducting the ground test of Indigenous High Thrust Cryogenic Engine at ISRO Propulsion Complex at Mahendragiri on April 28, 2015 at 1657 Hrs for a duration of 635 seconds. All the propulsion parameters during the tests were found satisfactory and closely matched with predictions. This ground test was preceded in the last few weeks, by four short duration tests of 5.5, 7.5, 20 and 30 seconds.

The Soviet/Russian RD-170 is among the most Powerful Rocket Engines in the World

The high thrust cryogenic engine is designed and realized by Liquid Propulsion Systems Centre (LPSC) at Valiamala with the support of Vikram Sarabhai Space Centre (VSSC) at Thiruvananthapuram. The engine assembly, integration and testing is carried out by ISRO Propulsion Complex (IPRC) at Mahendragiri. Indian Industries have significantly contributed in the realization of the cryogenic engine.

While ground tests conducted so far validate this the design adequacy and performance of the integrated engine, further demonstration tests are planned at engine and stage level to characterize the different performance parameters under various operating conditions. After completion of the tests, the indigenous high thrust cryogenic engine and stage are planned to be flight tested in GSLV Mk- III-D1 mission.
(Disclaimer:Text adapted from ISRO & other Internet Sources, please feel free to correct any mistakes)

@nair @Major Shaitan Singh @Chanakya's_Chant @MilSpec @SpArK @PARIKRAMA @The_Sidewinder @Hindustani78 @acetophenol @Abingdonboy @SarthakGanguly @Dillinger and others (Apology for not able to tag all interested members ).

So you wrote this article ... very good work ... :tup:

Highly informative and a better write-up than most other Indian reporters .
 
@kurup Mate, I was away from PDF since last two days so replying little late. The article is not written by me (didn't provide the link as I was not sure if links from this site were allowed by forum rules); Its taken from IDN as @Chanakya's_Chant pointed out with the link. I never intended to take credit for this :)
 
Last edited:

Is this site new or did they changed there appearance recently ??

@kurup Mate, I was away from PDF since last two days so replying little late. The article is not written by me (didn't provide the link as I was not sure if links from this site were allowed by forum rules); Its taken from IDN as @Chanakya's_Chant pointed out with the link. I never intended to take credit for this :)

No problem bro .

No link given and the disclaimer at the end made me confused ....... anyways a very informative article ....... thnx for sharing :-)
 
@kurup Mate, I was away from PDF since last two days so replying little late. The article is not written by me (didn't provide the link as I was not sure if links from this site were allowed by forum rules); Its taken from IDN as @Chanakya's_Chant pointed out with the link. I never intended to take credit for this :)

Doesn't matter as long as you are a decent poster - we will come to learn a lot from you - keep posting :tup:

Is this site new or did they changed there appearance recently ??



No problem bro .

No link given and the disclaimer at the end made me confused ....... anyways a very informative article ....... thnx for sharing :-)

New site - came up in 2014.
 

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