基于激波风洞的超声速磁流体动力技术实验系统

doi:CNKI:11-1929/V.20110427.1600.002

Abstract

Abstract: In order to perform magenetohydrodynamic (MHD) technical experiments, the experimental system needs to meet the following two conditions: one is supersonic or hypersonic flow; the other is that the flow must be conductivity. In this paper, basic composition, design methods, and debugging situation of a supersonic MHD technical experimental system based on shock tunnel are introduced. Mach number Ma=2 supersonic nozzle and testing section are designed; helium is used to drive argon gas, equilibrium contact surface operating mode is used for getting high temperature gas, and the conductive gas is obtained by adding ionization seed K₂CO₃ powder to the driven section. The following results are obtained: the effective testing time is about 9 ms by adjusting the length of driver section and driven section; the temperature in the 5th zone reaches over 3 500 K; due to short-time running, cooling problem of the nozzle and working section can be ignored; the conductivity of Ma=2 supersonic flow is 40 S/m, the magnetic interaction parameter Q is 0.174 under the conditions of p₁=3 kPa, L=0.2 m and B=2.0 T realized by electromagnet, while Q is 0.164 when p₁=1 kPa, L=1 m and B=0.5 T using permanent magnet. This experimental system could be used to perform preliminary experimental researches such as MHD flow control, MHD power generation and MHD acceleration.

Key words: shock tunnel, supersonic, magnetohydrodynamic, conductivity, magnetic interaction parameter

CLC Number:

V211.74⁺5

LI Yiwen, LI Yinghong, ZHANG Bailing, JIN Di, CHEN Feng, ZHU Tao. Supersonic Magnetohydrodynamic Technical Experimental System Based on Shock Tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(6): 1015-1024.

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Supersonic Magnetohydrodynamic Technical Experimental System Based on Shock Tunnel

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