This paper aims to numerically and experimentally analyze the effect of the micro-jet on the suction side (SS) of the transonic high-pressure turbine cascade, which could enable the possibility of the mass matching for turbine of the variable cycle engine (VCE) when it transforms working conditions according to flight demands. The experimental study had been conducted in a transonic and supersonic cascade wind tunnel to observe the influence of this kind of flow control technique on aerodynamic performance, operated at different exit Mach numbers. The nozzle guide vane with convergent-divergent passage was investigated in this paper. Two-dimensional steady simulations were performed to investigate the influence of the flow control method to exploit the potential of the application of this method in the design of high-pressure (HP) turbine for VCE.
Results of the numerical simulations and experiments indicated that micro-jet on the SS of the turbine blade would generate a separation zone near the jet slot, which would reduce the genuine throat area of the turbine passage and thus change the mass flow rate through the passage of the turbine cascade significantly. Also, velocity at the passage throat would be reduced due to the application of SS micro-jet, which would also contribute to the reduction of the mass flow rate through the turbine passage. However, extended total pressure loss was introduced with SS micro-jet.