Research on disturbance properties of suspensions near the injection area of moving jet

The equation of the suspension-gas non-streamwise complex disturbance velocity ratio near the injection area of moving jet was theoretically derived by using a phase-coupled model and stability theory. Then the ratio curves were obtained by the finite difference method based on the asymptotic method and the Euler conservative difference scheme. Analysis of the curves yielded conclusions on the disturbance properties of suspensions and effects of the natures of the flow-field and the properties of the suspensions on the suspensions ability to track the disturbed gas flow are presented in this paper. Projects supported by the State Education Commussion’s Trans-century Training Program Fund for Talents