Experimental investigation of an air-breathing pulse detonation turbine prototype engine

• An air-breathing pulse detonation turbine prototype engine was investigated by experiments.
• Two ignition methods on the engine were analyzed and discussed.
• Component characteristics were analyzed.
• Propulsive performances were given which show advantages over turbojet based on ideal Brayton cycle.

This article presents a prototype system of pulse detonation turbine engine which consists of two pulse detonation chambers (PDCs) and a turbocharger. Synchronous and asynchronous ignition methods are investigated with ignition frequency up to 20 Hz. Equivalence ratios are controlled around unity. Pressures in the PDCs show different detonation characteristics between these two ignition modes. Pressures upstream of the PDCs are also given. Detailed analyses of these pressure histories show that the two PDCs are coupled and these coupling effects become stronger for asynchronous ignition. Pressure downstream of the compressor is measured and three different compressor pressure ratios are defined according to this pressure. Pressure ratios and rotational speed are given as functions of ignition frequency and air flow rate which also reflect differences between these two ignition modes. Finally, the propulsive performances of the air-breathing pulse detonation prototype engine with synchronous and asynchronous ignition modes are provided. The maximum specific thrust of the system reaches 753 N s/kg which is 27% higher than that of the traditional engine based on ideal Brayton cycle.