OPEN ACCESS
The present paper aims to analyze the applicability of film cooling method to a rocket as a thermal protection. Lateral curvature effect on film cooling performance through a single row of cylindrical holes with different spanwise angles is investigated. Four different lateral curvature cases (C = ∞, 100, 60, 20) with four inclination angles of cooling injection holes (β= 35°, 45°, 55°, 65°) are considered. The ANSYS CFX has been used for this computational simulation. The turbulence is approximated by a shear stress transport model (SST). Detailed film effectiveness distributions are presented for several blowing ratios (0.5, 1 and 1.5). The numerical results are compared with experimental data.
computational fluid dynamics, heat and mass transfer, thermal protection, rocket nozzle, film cooling, propulsion
The corresponding author, GUELAILIA Ahmed, dedicates this paper to the memory of Professor ABIDAT Miloud.
[1] Coulbert CD. (1964). Selecting cooling techniques for liquid rockets for spacecraft. Journal of Spacecraft and Rockets 1(2): 129-139. http://doi.org/10.2514/3.27612
[2] Drost U, Bölcs A. (1999). Investigation of detailed film cooling effectiveness and heat transfer distributions on a gas turbine airfoil. ASME J. Turbomachinery 121: 233-242. http://doi.org/10.1115/1.2841306
[3] Ammari HD, Hay N, Lampard D. (1990). The effect of density ratio on the heat transfer coefficient from a film cooled flat plate. ASME J. Turbomachinery 112: 444-450. http://doi.org/10.1115/1.2927679
[4] Sinha AK, Bogard DG, Crawford ME. (1991). Film-cooling effectiveness downstream of a single row of holes with variable density ratio. ASME J. Turbomachinery 113: 442-449. http://doi.org/10.1115/1.2927894
[5] Guelailia A, Khorsi A, Hamidou MK. (2016). Computation of leading edge film cooling from a console geometry (converging slot hole). Thermophysics and Aeromechanics 23(1). http://doi.org/10.1134/S0869864316010042
[6] Khorsi A, Guelaili A, Hamidou MK. (2016). Improvement of film cooling effectiveness with a small downstream block body. Journal of Applied Mechanics and Technical Physics 57(4). http://doi.org/10.1134/S0021894416040106
[7] Tian K, Wang J, Zhanxiu C, Guelailia A. (2017). Effect of hole blockage configurations on film cooling in gas turbine components. Chemical Engineering Transactions 61. http://doi.org/10.3303/CET1761036
[8] Li Q, Wang J, Min C, Tian K, Tian L, Sundén B. (2017). Effect of an upstream unconnected bulge on film cooling. Chemical Engineering Transactions 61. http://doi.org/10.3303/CET1761035
[9] Sargison JE, Guo SM, Oldfield MLG, Lock GD, Rawlinson AY, Xu DCh. (2002). A converging slot-hole film-cooling geometry. Part 2. Transonic nozzle guide vane heat transfer and loss. ASME J. Turbomachinery 124: 461−471. http://doi.org/10.1115/1.1459736
[10] Goldstein RJ, Eckert ERG, Chiang HD, Elovic E. (1985). Effect of surface roughness on film cooling performance. ASME J. Engng Gas Turbines Power 107: 111−116. http://doi.org/ 10.1115/1.3239669
[11] Schmidt DL, Bogard DG. (1996). Effects of free-stream turbulence and surface roughness on film cooling. ASME Paper. http://doi.org/10.1115/96-GT-462
[12] Schmidt DL, Sen B, Bogard DG. (1996). Effects of surface roughness on film cooling. ASME Paper. http://doi.org/10.1115/96-GT-299
[13] Yuen CHN, Martinez-Botas RF. (2003). Film cooling characteristics of a single round hole at various streamwise angles in a crossflow. Part I. Effectiveness. Int. J. Heat Mass Transfer 46: 221−235. http://doi.org/10.1016/S0017-9310(02)00274-0
[14] Yuen CHN, Martinez- RF. (2003). Film cooling characteristics of a single round hole at various streamwise angles in a crossflow. Part II. Heat transfer coefficients. Int. J. Heat Mass Transfer 46: 237−249. http://doi.org/10.1016/S0017-310(02)00273-9
[15] Yuen CHN, Martinez-Botas RF. (2005). Film cooling characteristics of rows of round holes at various streamwise angles in a crossflow. Part I. Effectiveness. Int. J. Heat Mass Transfer 48: 4995−5016. http://doi.org/10.1016/j.ijheatmasstransfer.2005.05.019
[16] Yuen CHN, Martinez-Botas RF. (2005). Film cooling characteristics of rows of round holes at various streamwise angles in a crossflow. Part II. Heat transfer coefficients. Int. J. Heat Mass Transfer 48: 5017−5035. http://doi.org/10.1016/j.ijheatmasstransfer. 2005.05.020
[17] Lucas JG, Golladay RL. (1963). An experimental investigation of gaseous film cooling of a rocket motor. NASA TN 0-1988.
[18] Kumar AL, Pisharady JC, Shine SR. (2015). Effect of injector configuration in rocket nozzle film cooling. Heat Mass Transfer. http://doi.org/10.1007/s00231-015-1590-7
[19] McCall JF, Branam RD. (2009). Effects of radial curvature on net heat flux reduction in a film-cooled rocket. 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, AIAA, 2009-1586. http://doi.org/10.2514/6.2009-1586
[20] Nasir H, Ekkad SV, Acharya S. (2001). Effect of compound angle injection on flat surface film cooling with large streamwise injection angle. Experiment Thermal Fluid Sci. 25(1/2): 23–29. http://doi.org/10.1016/S0894-1777(01)00052-8
[21] Menter FR. (1994). Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J. 32(8): 1598–1605. http://doi.org/10.2514/3.12149