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Numerical Simulation of the two pulse detonation engine

Author: QiuYanJie
Tutor: WuXiaoSong
School: Nanjing University of Technology and Engineering
Course: Aerospace Propulsion Theory and Engineering
Keywords: Two pulse detonation engine Shock wave Detonation initiation Cavity Jet parameters Multi-cycle Knock frequency
CLC: V235
Type: Master's thesis
Year: 2011
Downloads: 22
Quote: 0
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Abstract


Pulse detonation engine (PDE, Pulse Detonation Engine) is a new concept of detonation combustion - based propulsion system , is widely considered to be the 21st century 's most revolutionary development the aerospace power plant one . The effective ignition is one of the key technologies of the pulse detonation engine . The initiation of the two pulse detonation engine based on the shock to the formation of the high-temperature and high-pressure area in the resonant cavity , thereby detonating gas mixture . In this paper, the numerical simulation , conducted a study of this type of engine cavity flow field , numerical methods coupled explicit algorithm , and the chemical reaction model using the single-step hydrogen / air chemical reaction . This article consists of three main parts: the first , to simulate the combustion reaction in the case of the ellipsoid parabolic , conical , straight tube -type structure of four different cavity flow field development process , and based on research chamber depth for the influence of the temperature, pressure, the two high-temperature high-pressure region within the resonant cavity successively formed . The study found that the parabolic and ellipsoid exist optimum chamber depth , and the parameters are within the conical and straight tube-type high - temperature high-pressure region is formed in the vicinity of the apex changes linearly with the chamber depth . The second part, on the basis of the pre-filled with the fuel of the resonant cavity by numerical simulation of the impact of different the incident temperature and incident pressure axis detonating . Select the appropriate parameters of the entrance , on the basis of successful implementation of the axis of initiation , and captured again focus in the development process of the flow field . Further studies showed that when the jet pressure is lower than a certain critical value , then only at the apex of detonation. The third part , by the installation of the expansion section and the separation of the jet fuel supply to achieve a multi-cycle the two pulse detonation engine working process , the engine in a loop to stabilize the knock frequency of 1.9KHz .

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Air jet engine
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