脉冲爆震涡轮发动机增推装置性能试验

doi:10.7527/S1000-6893.2015.0083

Abstract

Abstract:

To acquire experimental propulsive performance of pulse detonation turbine engine(PDTE), thrust augmentation devices, such as converge/diverge nozzles and ejector, are installed on the turbine exit of two-tube PDTE experimental system. Experimental investigations are carried out to research the influences of thrust augmentation devices on the working condition and propulsive performance of PDTE. The PDTE experimental system is in the self-airbreathing working mode with working frequency from 10 Hz to 20 Hz. Liquid gasoline is used as fuel. Results show that the turbine speed, compression ratio and flow of compressor are all decreased with different degrees when converge/diverge nozzles are installed to the PDTE experimental system. However, the engine thrust is increased with the use of nozzles. Compared with the system without nozzle(thrust of which is 114.95 N at working frequency 20 Hz), the maximum thrust of the system with nozzle is 143.3 N and the thrust augmentation is 24.7%. And the maximum specific thrust is 749.87 N·s/kg. The thrust of the PDTE experimental system can be further increased with the installation of ejector to the system with nozzle. The maximum thrust at this condition is 200.67 N and the thrust augmentation is 39.8%. And the thrust augmentation can still be increased with the increase of working frequency.

Key words: pulse detonation turbine engine, nozzle, ejector, propulsive performance, air breathing

CLC Number:

V231.2

QIU Hua, XU Zeyang, ZHENG Longxi, DUAN Xiaoyao. Tests of pulse detonation turbine engine performance with thrust augmentation devices[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(2): 522-532.

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Tests of pulse detonation turbine engine performance with thrust augmentation devices

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