In this project is the gas flow characteristic of a helicopter engine e xhaust and to derive an optimized geometry for the e xhaust duct with minimum pressure loss using CFD analysis. In this project, the variables to be analyzed are the in let static pressure, velocity and temperature of the e xhaust gas at the exit of the e xhaust duct. Cylindrical e xhaust ducts of various dimensions are modeled by changing the primary and secondary inlet area and the e xhaust geometry is optimized based on the CFD results. For the same optimized area of primary and secondary inlet, divergent e xhaust duct is modeled and analyzed for various divergent angles. Parametric studies were carried out for a better comparison between cylindrical and divergent ducts for the better thermal efficiency.
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