Abstract
Aerodynamic design of turbomachines inside a small turboshaft engine has been performed. The engine is a twin spool turboshaft engine, which consists of a gas generator and axial type power turbine followed by. The gas generator consists of a centrifugal compressor-radial turbine spool. To minimize specific fuel consumption of the engine, heat exchange occurs between compressor outlet air and power turbine exhaust gas. To supply sufficiently decelerated and radially de-swirled flow to the heat exchanger, two-staged cascade diffuser was introduced at the compressor diffuser row. Mass flow rate is controlled by the radial turbine nozzle throat. The design results showed that aerodynamic performances are higher than design requirements. For this reason, stage matching between adjacent components is required. In this study, stage matching between the radial turbine and the power turbine was considered. CFD result revealed that flow capacity of the axial turbine is high for adequate stage matching, so flow path has been adjusted to produce required power both from radial and axial turbines.
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