A Subsonic (Turboprop) Engine Inlet Design and Optimization

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2022-1
Özer, Sevda
Intake is a duct designed to convey air to the engine compressor, with low flow distortions and a suitable Mach number for stable operations; it decelerates the stream and increases its static pressure. Unfortunately, this pressure recovery implies an adverse gredient along the duct that leads to flow seperation on walls causing losses and non-uniformities [1]. Within this study a turboprop engine air inlet geometrical optimization has been done. The details of the root cause of the engine integration losses are explained, then the air inlet design considering less engine installation loss (pressure loss) and drag is given. During the analysis, three air inlet design input parameter configuration matrix has been used to generate the alternative air inlet models. These three parameters are the diffuser inlet area, diffuser side wall angle and diffuser length. Then with each geometry a Computational Fluid Dynamics (CFD) analysis was performed to obtain the corresponding pressure loss and induced drag emerging due to bigger sized inlet. Within the last part of the sequence, inlet optimisation is performed among the generated alternative inlet geometries. The performance evaluation of the air inlet is based on the engine installation loss, generated engine thrust and induced drag. During the optimization these two parameters are used as a target. In the end of the study, optimized geometry performance improvement is calculated and compared with the referenced geometry to present the improvement percentage.

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Citation Formats
S. Özer, “A Subsonic (Turboprop) Engine Inlet Design and Optimization,” M.S. - Master of Science, Middle East Technical University, 2022.