Astronomy & Space Sciences
Title : | Analysis of throat film cooling for semicryogenic thrust chamber |
Area of research : | Astronomy & Space Sciences |
Focus area : | Combustion modelling with liquid film cooling |
Details
Executive Summary : | The 2000 kN Semi-cryogenic engine is a high thrust engine and generates high thermal load on the thrust chamber wall. Hencethe thrust chamber is cooled by film cooling along with regenerative cooling. The throat region of thrust chamber is subjected to maximum heat flux. Hence positive film cooling is to be ensured in this portion to reduce the heat flux.The conventional film coolant injected near the injector end is not sufficient to keep the throat wall temperature below safe temperature limit. This calls for additional film cooling provision near the throat region.Isrosene (fuel used for semicryo engine: equivalent to RP1) is used for both film cooling as well as regenerative cooling in liquid state. The film coolant, after injection in to the thrust chamber takes part in combustion, hence film coolant layer depletes gradually. For safe operation of engine, a positive film coolant is an essential requirement. This necessitates detail modelling (considering proper reaction steps, species and reaction rates) of phase change of film coolant and participation in combustion. Based on the CFD results an empirical correlation is also to be formulated for predicting the film coolant thickness in the
thrust chamber for varying operating parameters. |
Co-PI: | Shri P Baiju, Liquid Propulsion Systems Centre (LPSC), Valiamala |
Organizations involved
