CFD |Thermal| Machine Learning Engineer
Project Summary:
Six month Project (Bachelor Project) done in Indian Space Research Organisation(ISRO): High altitude rocket motors(stage) needs to be tested at sea level for high altitude conditions. This requires simulating low back pressure for full flow condition(with out separation) in nozzle which
is achieved by reducing back pressure by self ejecting second throat exhaust diffuser (STED). The objective was to find the optimum contraction ratio(Ast/Ad) of diffuser(STED) for nozzle area ratio=100 to get minimum starting pressure. Experimental work was done in SHAR, ISRO. For Numerical computation, Gambit was used for meshing and Ansys-Fluent solver used for analysis of the flow. Post-processing was done in MS Excel, Matlab.
Some Results:
Grid of nozzle with 100 Area Ratio and with STED contraction ratio of 0.5 done using Gambit
Close view of grid of Nozzle and STED
Mach contour for different contraction ratios
Pressure recovery along the diffuser form nozzle exit for different motor pressures for contraction ratio 0.45
Mach no variation along the axis for contraction ratio 0.45
Schematic of Cold flow set up for 100 AR without vacuum chamber
Photographic view of cold flow test set up in SHAR-ISRO