Experimental study on performance of blockerless cascade thrust reverser

The experimental investigtion of blockerless cascade thrust reverser based on secondary injection was conducted on the dual flow transonic and supersonic cascade test facility. Effect of parameters including fan outlet pressure ratios, secondary pressure ratios, secondary injection positions and secondray injection angles on the performance of blockerless cascade thrust resver were studied. The final results show that fan outlet pressure ratios and secondary pressure ratios has some complex relationship. When secondary pressure ratio less than a certain value, cascase reverse mass flow decreases with the increase of fan outlet pressure ratio, however if secondary pressure ratio esceed the value, it would present a opposite trend. In the whole experimental conditions, there exist a best secondary injection position (58.77mm≤Xj≤ 77.87mm) with injection angle (θ=60°) achieving highest thrust reverse.