Astronomy & Space Sciences
Title : | Ignition modelling of semi cryogenic engine |
Area of research : | Astronomy & Space Sciences |
Focus area : | Ignition modeling |
Details
Executive Summary : | 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. |
Co-PI: | Dr. K.S. Bijukumar, Liquid Propulsion Systems Centre (LPSC), Valiamala |
Organizations involved
