An attempt to reduce supersonic jet noise is carried out by using two steady microjets in a round jet. The jet is issued from a round sonic nozzle with an exit diameter of 10 mm. Two micro-nozzles with an inside diameter of I mm each are installed on the exit plane at an angle of 45 ° relative to the main jet axis. Far-field noise was measured at 40diameters off the jet axis. The angle between a microphone and the jet axis is 30° or 90 °. For an injection rate of 4-6% of the main jet, screech tones were completely suppressed by the microjets. The reduction in the ovelall sound pressure levels were 2.4 and 2.7 dB for 90 ° and 30 ° measuring directions, respectively. However, the enhancement of mixing/spreading of the jet by the microjet was negligible. The reduction of noise is probably due to distorted shock cell structures and/or deformed large scale vortical structures by the microjets .