In order to figure out how the inlet velocity distortion and the bypass ratio effect on the performance of lobed mixer,a two-flow annular axisymmetric afterburner test model with inlet distortion orifice plates was designed and a five-hole probe combined with a three-dimensional displacement equipment was employed to measure the three-dimensional flow field of different inlet velocity distortion and bypass ratio behind lobed mixer planes. The results show that with the increases of distance from the outlet of lobed mixer,the mixing velocity of core and bypass will increase at first then descend, and the total pressure recovery coefficient will decline,while the mixing efficiency and thrust gain will increase. The results also show that the increases of bypass ratio will enlarge the range of streamwise vortex and low temperature,while the mixing homogeneity,mixing efficiency and total pressure recovery coefficient will decline. When the inlet velocity distortion peak is on the top,the airflow will be accelerated mixing which is beneficial to the thrust gain and the total pressure recovery coefficient will be higher,and the mixture efficiency will be higher with a small bypass ratio. When the peak of inlet velocity distortion is at the bottom,both the wall static pressure of diffuser and the static pressure of center cone are relatively high.
Journal of Propulsion Technology