Ignition Test of Solid Fuel Ramjet Combustor

Abstract

The aim of this work was to measure and reduce the "spontaneous" ignition delay of solid fuel ramjet combustor in a 155 mm gun-propelled artillery round application. Fuel-rich propellant consist by Hydroxyl terminated poly butadiene (HTPB), Ammonium Perchlorate(AP) and Aluminium(Al) was selected as a ramjet fuel. And ignition test of a solid fuel ramjet combustor was conducted. In the combustor, the oxidant that burns fuel is oxygen in the heated and compressed air. It is achieved by the shock wave located in the diffuser. The "ethanol blended H2O2 vitiated air heater" emulates this air condition in the combustor. When blended hydrogen peroxide passes the catalytic bed, it generates hot gas which satisfies the oxygen condition, 21 mol.%. Ignition support material was adapted to reduce ignition delay. It is consisted by Boron Potassiumnitrate(BKNO3), Nitrocellulose(NC) and AP/HTPB based composite propellant. In the test, ignition delay was measured to 1.74 second and flame was maintained.