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Ignition modelling of semi cryogenic engine

Implementing Organization

CO-Principal Investigator
Dr. K.S. Bijukumar
Liquid Propulsion Systems Centre (LPSC), Valiamala

About

In order to enhance the payload capability of GSLV MkIII launcher, a 2000kN thrust Semi cryogenic engine is under development. Propellants used are Liquid Oxygen (LOX) and Isrosene (Refined kerosene). In order to start ignition, Triethyl aluminum (TEA) and Triethyl boron (TEB) is used as igniter fuel. Ignition modeling of this igniter fuel with oxygen and combustion modeling of Isrosene and Oxygen has to be carried out to assess the following aspects: Igniter fuel quantity requirement, ignition characteristics such as time delay, peak pressure etc, engine propellant flow requirement and transient build up for sustaining the ignition.

Related Research

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Funding Organization
Funding Organization
Department of Space (DoS)
Quick Information
Area of Research
Astronomy & Space Sciences
Focus Area
Ignition modeling
Status
Ongoing
Contact
NA
Output
No. of Research Paper
00
Technologies (If Any)
00
No. of PhD Produced
00
No. of Patents
Filed : 00
Grant : 00
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