Udding of Regenerative type heat transfer in liquid fuel missiles engine

Udding of Regenerative type heat transfer in liquid fuel missiles engine

Document Type : Original Article

Abstract

Heat transfer plays a major role in the design and performance of missiles and vehicles that have rocket driving. The main importance of this discussion is related to the safety range missile materials, especially in areas such as the combustion chamber and nozzle, which are under critical heat. Only one failure is enough to interfere with the operation of missiles. It may also be due to excessive heat in the nozzle throat, a portion of the sheet metal locally damaged. In which case the exhaust gas flow becomes asymmetrically, which led to the creation of inappropriate force vector direction. This leads to an error in the missile guidance to the target and a lot of fuel consumed on the spacecraft to correct its path by secondary driving system. In this project the amount of heat transferred to the chamber for different sections of engine during the simulation by software is calculated, also the coolant conditions and temperatures have been calculated in accordance with existing heat and cooling operation performed in each section. For this purpose, the engine divided into four parts, the combustion chamber, the convergent nozzle, throat nozzle and the divergent nozzle. The rate of heat transferred from the gas chamber (according to the conditions of gas in different sections) as well as the chamber temperature in the vicinity of the coolant and coolant temperature calculated for different sections of each section. Notably, in this research, ANSYS software package is used to create geometry, mesh and simulations.

Keywords

missiles

regenerative heat transfer

combustion chamber

nozzle

20.1001.1.28211553.1401.1.2.4.3

Subjects

Radar/thermodynamics/heat transfer/fuel and combustion/energy/...

[1] D. K. Huzel, “Modern engineering for design of liquid-propellant rocket engines”, American Institute of Aeronautics and Astronautics, pp. 156-170, 1992.

[2] G. P. Sutton and O. Biblarz, “Rocket propulsion elements”; 9th edition, John Wiley & Sons, pp. 261-280, 2016.

[3] R. Shine and S. Shri, “Review on film cooling of liquid rocket engines”, Propulsion and Power Research, vol. 7, pp. 1-18, 2018.

[4] C. Münch and O. Métais, “Turbulence in cooling channels of rocket engines: Large Eddy Simulations”, Comptes Rendus Mecanique, vol. 333, pp. 574-579, 2005.

[5] S. K. Kim, M. Joh and T. S. Park, “Multidisciplinary simulation of a regeneratively cooled thrust chamber of liquid rocket engine: Turbulent combustion and nozzle flow”, International Journal of Heat and Mass Transfer, vol. 70, pp.1066-1077, 2014.

[6] Y. Torres, L. Stefanini and D. Suslov, “Influence of curvature in regenerative cooling system of rocket engine”, in Progress in Propulsion Physics, vol. 1, pp. 171-184, 2009.

[7] J. W. Li, Y. Liu and L. Z. Qin, “Numerical Simulation of Flow and Heat Transfer in Round-to-Rectangular Nozzles”, Numerical Heat Transfer Applications, vol. 51, pp. 267-291, 2007.

[8] H. Zhang, Y. He and W. Tao, “Numerical study of film and regenerative cooling in a thrust chamber at high pressure”, Numerical Heat Transfer Applications, vol. 52, pp. 991-1007, 2007.

[9] V. Yang, M. Habiballah, J. Hulba and M. Popp, “Liquid Rocket Combustion Devices: Aspects of Modeling, Analysis and Design”, AIAA Progress in Astronautics and Aeronautics Series, Washington DC, 2005.

[10] P. M. Sforza, “Propulsion Principles and Engine Classification”, Theory of Aerospace Propulsion, 2th ed., 2017.

[11] S. Marian and R. Ioan, “Design and manufacturing process for a ballistic missile”, Scientific Bulletin, vol. 42, pp.141-146, 2016.

[12] “Ansys Fluent Theory Guide”, Version 15.0, 2013.

[13] H. S. Frank, “The Physics of Astrophysics: Gas dynamics”, University Science Books, pp. 350-440, 1991.

[14] “Ansys Fluent User’s Manual”, Version 15.0, 2013.

[15] “Ansys ICEM CFD User’s Manual”, Version 15.0, 2013.

[16] L. Davidson, “Fluid mechanics, turbulent flow and turbulence modeling”, Chalmers University of Technology, Goteborg, Sweden, 2017.

[17] Aamir, Sh.;“Thermophysical properties of complex materials”, Books on Demand, pp. 68-102, 2020.

[18] Zh. T. Zhou, C. F. Zhao, G. G. Le., “Numerical Studies on Flow field Characteristics of Four-Engine Rockets Impinging Jet with Different Flame Deflectors”, Journal of Physics: Conference Series, vol. 1507, no. 8, pp. 1-3, 2020.