Modern aero-engines require a high cycle temperature for effective performance. Particular attention is paid to the ICAS (internal cooling air system), particularly the air-bleed system, where the cooling air is bled from the compressor platform to cool down the turbine discs but faces an internal losses problem. Turbines are the elemental power supply of aero-engine and always exposed to high temperature. Internal pressure losses will lead to shortage of air from compressor to turbine disk for cooling purpose, thus deteriorating turbine’s performance and finally limiting their lifespan.To simulate the flow in the air-bleed system in an aero-engine, a co-rotating cylindrical cavity with two steel discs is used as a simplified model. In the present study, we found that oblong nozzles at the shroud improved flow conditions and are 30–50% better than circular ones at reducing pressure losses. Furthermore, we discuss the combined effect of vortex reducers and nozzles under a range of different values of λT (which decided by inertial factor of internal flow and rotational factor of disks), and found them to have a positive effect only when λT is in a specific range. Compared with the whole vortex reducer configuration (long tubes ×15), particular attention is focused on the combined vortex reducer configuration with long-short matched tubes, (long tubes ×10 and short tubes ×5 arranged interlacely in turbine cavity) which is designed to reduce weight and vibration but still has high potential capability to reduce pressure losses. To analyse the experimental data, Ro is adopted to describe the pressure losses instead of the conventional use of λT. This is suitable particularly in the cavity with tubes. Test rig results concerning the pressure drop for different configurations can be referenced by aero-engine designers for convenient and optimized industrial manufacture.
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