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Plasma Sci. Technol. ›› 2018, Vol. 20 ›› Issue (6): 065511.doi: 10.1088/2058-6272/aab2a4

• Plasma Technology • Previous Articles     Next Articles

Numerical and experimental investigation of plasma plume deflection with MHD flow control

Kai ZHAO (赵凯)1,2, Feng LI (李锋)1, Baigang SUN (孙佰刚)3, Hongyu YANG (杨宏宇)1, Tao ZHOU (周韬)1 and Ruizhi SUN (孙睿智)1   

  

  1.   1 School of Energy and Power Engineering, Beihang University, Beijing 100191, People’s Republic of China
     2 School of Aviation Operations and Services, Aviation University of Air Force, Changchun 130022, People’s Republic of China    
    3 Air Force Command College, Beijing 100191, People’s Republic of China
  • Received:2017-10-18 Published:2018-02-27
  • Supported by:

     

    This project is supported by National Natural Science Foundation of China (No. 90716025).

Abstract:

 This paper presents a composite magneto hydrodynamics (MHD) method to control the low-temperature micro-ionized plasma flow generated by injecting alkali salt into the combustion gas to realize the thrust vector of an aeroengine. The principle of plasma flow with MHD control is analyzed. The feasibility of plasma jet deflection is investigated using numerical simulation with MHD control by loading the User-Defined Function model. A test rig with plasma flow controlled by MHD is established. An alkali salt compound with a low ionization energy is injected into combustion gas to obtain the low-temperature plasma flow. Finally, plasma plume deflection is obtained in different working conditions. The results demonstrate that plasma plume deflection with MHD control can be realized via numerical simulation. A low-temperature plasma flow can be obtained by injecting an alkali metal salt compound with low ionization energy into a combustion gas at 1800–2500 K. The vector angle of plasma plume deflection increases with the increase of gas temperature and the magnetic field intensity. It is feasible to realize the aim of the thrust vector of aeroengine by using MHD to control plasma flow deflection.

Key words: MHD, plasma, ionization degree, thrust vector, aero engine