Numerical study of gas–liquid two-phase flow and noise characteristics for a water injection launching concentric canister launcher
Author:
Zou Huajie1, Yang Fengbo2, Cai Fuhai1, Shi Qiongyan1
Affiliation:
1. Changzhou Vocational Institute of Mechatronic Technology , Changzhou 213164 , China 2. College of Mechanical and Electronic Engineering , Nanjing Forestry University , Nanjing 210037 , China
Abstract
Abstract
In view of the poor thermodynamic environment problem of the self-powered launch of land-based concentric canister launcher (CCL), the launching scheme of injecting water at the bottom of launching tube is adopted to improve the thermodynamic environment of the launching system fundamentally. The solution program for liquid water vaporization is compiled and embedded into the homogeneous gas–liquid two-phase flow model, the source phase corrections of the momentum equation and the energy equation are also performed, and then the three-dimensional gas–liquid two-phase fluid dynamics model is established for the land-based CCL; analysis shows that the improvement of the thermal environment of the 35° and 45° water injection schemes is more better among these schemes. So coupling the mixture model, vaporization program and FW–H (Ffowcs Williams Hawkings) noise model, the noise distribution law in the bottom of the launcher cube for 35 and 45 water injection angles is discussed; in the intermediate frequency range, the −45° water injection scheme is about 2–10 dB higher than the noise signal of the −30° water injection scheme. Finally, it is recommended to optimize the overall thermal environment of the CCL by using the −30° preferred water injection scheme with both cooling effect and noise control.
Publisher
Walter de Gruyter GmbH
Subject
Applied Mathematics,General Physics and Astronomy,Mechanics of Materials,Engineering (miscellaneous),Modeling and Simulation,Computational Mechanics,Statistical and Nonlinear Physics
Reference36 articles.
1. E. Geery and R. Greenwood, “Water injection for rapid cooling of a flow of rocket exhaust gases,” 5th Propulsion Joint Specialiat, American Institute of Aeronautics and Astronautics, 1969. 2. E. L. Geery and M. J. Margetts, “Penetration of a high velocity gas stream by a water jet,” 4th Propulsion Joint Specialist Conf., American Institute of Aeronautics and Astronautics, 1968. 3. M. J. Miller, J. H. Koo, F. M. Sickler, et al.., “Effect of water to ablative perform under solid rocket exhaust environment,” 29th Joint Propulsion Conf. and Exhibit, American Institute of Aeronautics and Astronautics, 1993. 4. S. Sankaran, J. K. Ignatius, R. Ramkumar, et al.., “Suppression of high Mach number rocket jet noise by water injection,” J. Spacecraft Rockets, vol. 46, no. 6, pp. 1164–1170, 2012. 5. Y. Jiang, Z. Fan, and X. Zhang, “Experimental study on flow field of high temperature supersonic impinging jet injected by water,” J. Exp. Fluid Mech., vol. 25, no. 4, pp. 32–36, 2011.
|
|