A novel method for flame stabilization in a strut-based scramjet combustor

For successful operation of propulsion system of an air-breathing hypersonic aircraft, flame stabilization in its scramjet combustor is very critical. In this paper, a novel strut is proposed for flame stabilization in a scramjet combustor. The novel strut is a modification of the traditional strut with the angles of its rear part enlarged. Employing the two-dimensional compressible multi-species Navier–Stokes equations and a one-step hydrogen–air reaction model, six simulation cases are performed. An analysis of the simulations is conducted to explain the stabilization of the flame by the proposed novel strut. The shock waves induced by the rear part of the novel strut cause a high-temperature and high-pressure region for combustion and an effective total pressure loss. The strong shock waves affect only the nearby region of the strut for the reason that only a small part of the wedge is wedge angle enlarged. The novel strut is thus able to stabilize the flame behind it and can be used as a flame holder in a scramjet combustor.