Thrust measurement method verification and analytical studies on a liquid-fueled pulse detonation engine  

作　　者：Lu Jie Zheng Longxi Wang Zhiwu Peng Changxin Chen Xinggu 

机构地区：[1]School of Power and Energy, Northwestern Polytechnical University

出　　处：《Chinese Journal of Aeronautics》2014年第3期497-504,共8页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (No. 51306153);the Natural Science Foundation of Shanxi Province of China (No. 2010JQ7005);Doctoral Fund of Ministry of Education of China (No. 20116102120027);Northwestern Polytechnical University Foundation for Fundamental Research (No. NPU-FFRJCY20130129)

摘　　要：In order to test the feasibility of a new thrust stand system based on impulse thrust mea- surement method, a liquid-fueled pulse detonation engine （PDE） is designed and built. Thrust per- formance of the engine is obtained by direct thrust measurement with a force transducer and indirect thrust measurement with an eddy current displacement sensor （ECDS）. These two sets of thrust data are compared with each other to verify the accuracy of the thrust performance. Then thrust data measured by the new thrust stand system are compared with the verified thrust data to test its feasibility. The results indicate that thrust data from the force transducer and ECDS system are consistent with each other within the range of measurement error. Though the thrust data from the impulse thrust measurement system is a litter lower than that from the force transducer due to the axial momentum losses of the detonation jet, the impulse thrust measurement method is valid when applied to measure the averaged thrust of PDE. Analytical models of PDE are also discussed in this paper. The analytical thrust performance is higher than the experimental data due to ignoring the losses during the deflagration to detonation transition process. Effect of equivalence ratio on the engine thrust performance is investigated by utilizing the modified analytical model. Thrust reaches maximum at the equivalence ratio of about 1.1.In order to test the feasibility of a new thrust stand system based on impulse thrust mea- surement method, a liquid-fueled pulse detonation engine （PDE） is designed and built. Thrust per- formance of the engine is obtained by direct thrust measurement with a force transducer and indirect thrust measurement with an eddy current displacement sensor （ECDS）. These two sets of thrust data are compared with each other to verify the accuracy of the thrust performance. Then thrust data measured by the new thrust stand system are compared with the verified thrust data to test its feasibility. The results indicate that thrust data from the force transducer and ECDS system are consistent with each other within the range of measurement error. Though the thrust data from the impulse thrust measurement system is a litter lower than that from the force transducer due to the axial momentum losses of the detonation jet, the impulse thrust measurement method is valid when applied to measure the averaged thrust of PDE. Analytical models of PDE are also discussed in this paper. The analytical thrust performance is higher than the experimental data due to ignoring the losses during the deflagration to detonation transition process. Effect of equivalence ratio on the engine thrust performance is investigated by utilizing the modified analytical model. Thrust reaches maximum at the equivalence ratio of about 1.1.

关 键 词：Analytical model Equivalence ratio Impulse method Liquid fuel Pulse detonation engine Thrust measurements 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程] TP274[自动化与计算机技术—检测技术与自动化装置]