Abstract: The research on rotating detonation turbine engine (RDTE) is attracting much attention in recent years, but the high-frequency pressure oscillation always exists at the rotating detonation combustor (RDC) exit, which could reduce the operation efficiency and the working life of turbine. Experiments were performed on a structure combining RDC and turbine guide vane based on the propagation characteristic of rotating detonation wave (RDW). Hydrogen, which was used as fuel, was injected into chamber through 120 orifices uniformly distributed in front of combustor, and air, which was functioned as an oxidiser, was injected into combustion chamber through a radial annular slot. The product of detonation directly flowed into guide vane after the detonation wave being initiated in the combustor. Results show that the velocity of detonation wave initially increases and then decreases with the increase of equivalence ratio. There is oscillation pressure at the exit of guide vane, which has the same oscillation frequency with detonation wave in combustor, and the oscillation pressure is reduced by 64% after passing through the guide vane. The relative standard deviation of RDW propagation velocity initially decreases and then increases, and the loss of velocity will be small when the detonation wave propagates stably.