In rocket engine nozzle design, flow separation is essential and, given the high temperatures and pressures in the thrust chamber, regenerative cooling is critical for maintaining the nozzle wall's integrity. This passage provides a summary of an in-depth numerical analysis of boundary layer separation and heat transfer within a 30°-15° cooled nozzle. The performance of the SST-V turbulence model under these conditions is assessed numerically. A variety of factors are investigated, including wall temperature, turbulent Prandtl number, and constant specific heat ratios (spanning 1.31 to 1.4 for constant fluid properties of N2O, CH4, Cl2, and air). Furthermore, variable specific heat ratios (from 1.39 to 1.66 for variable fluid properties of air, CH4, O2, and Helium) are examined, along with other parameters that affect the location of separated flow and the local wall heat transfer.
Arnold R, Suslov D, Haidn O. Influence Parameters on Film Cooling Effectiveness in a High Pressure Subscale Combustion Chamber. 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics; 2009.
2.
Back LH, Massier PF, Gier HL. Convective heat transfer in a convergent-divergent nozzle. International Journal of Heat and Mass Transfer. 1964;7(5):549–68.
3.
Baron J, Durgin F. An experimental investigation of heat transfer at the boundaries of supersonic nozzles. 1954;
4.
Khaled B, Khadidja K. NUMERICAL INVESTIGATION OF SUPERSONIC FLOW SEPARATION IN THRUST-OPTIMIZED CONTOUR ROCKET NOZZLE. Journal of the Serbian Society for Computational Mechanics. 2022;16(2):43–55.
5.
Bensayah K, Hadjadj A, Bounif A. Heat Transfer in Turbulent Boundary Layers of Conical and Bell Shaped Rocket Nozzles with Complex Wall Temperature. Numerical Heat Transfer, Part A: Applications. 2014;66(3):289–314.
6.
Betti B, Bianchi D, Nasuti F, Martelli E. Chemical Reaction Effects on Wall Heat Flux in Liquid Rocket Thrust Chambers. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. American Institute of Aeronautics and Astronautics; 2014.
7.
Campbell C, Farley J. Performance of several conical convergent-divergent rocket type exhaust nozzles. 1960;
8.
CUFFEL RF, BACK LH, MASSIER PF. Transonic flowfield in a supersonic nozzle with small throat radius of curvature. AIAA Journal. 1969;7(7):1364–6.
9.
Daimon Y, Negishi H, Yamanishi N, Nunome Y, Sasaki M, Tomita T. Combustion and Heat Transfer Modeling in Regeneratively Cooled Thrust Chambers (Optimal Solution Procedures for Heat Flux Estimation of a Full-Scale Thrust Chamber). 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics; 2012.
10.
Délery J, Marvin J. Shock-Wave boundary layer Interactions. 1986;
11.
Frank G, Pfitzner M. Investigation of the heat transfer coefficient in a transpiration film cooling with chemical reactions. International Journal of Heat and Mass Transfer. 2017;113:755–63.
12.
Kim JG, Lee JW, Kim KH. Investigation on the Characteristics of Plume-Induced Flow Separation and Wall Heat Transfer. Journal of Spacecraft and Rockets. 2012;49(1):189–92.
13.
Kolozsi J. An Investigation of Heat Transfer through the Turbulent Boundary Layer in an Axially Symmetric Convergent-Divergent Nozzle. 1958;
14.
Kurtbaş İ. The effect of different inlet conditions of air in a rectangular channel on convection heat transfer: Turbulence flow. Experimental Thermal and Fluid Science. 2008;33(1):140–52.
15.
Leccese G, Bianchi D, Betti B, Lentini D, Nasuti F. Convective and Radiative Wall Heat Transfer in Liquid Rocket Thrust Chambers. Journal of Propulsion and Power. 2018;34(2):318–26.
16.
Lebedev VP, Lemanov VV, Terekhov VI. Film-Cooling Efficiency in a Laval Nozzle Under Conditions of High Freestream Turbulence. Journal of Heat Transfer. 2005;128(6):571–9.
17.
Ljuboja M, Rodi W. Prediction of Horizontal and Vertical Turbulent Buoyant Wall Jets. Journal of Heat Transfer. 1981;103(2):343–9.
18.
MACCORMACK R. Current status of numerical solutions of the Navier-Stokes equations. 23rd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics; 1985.
19.
Miranda A, Naraghi M. Analysis of Film Cooling and Heat Transfer in Rocket Thrust Chamber and Nozzle. 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics; 2011.
20.
Ragsdale WC, Smith JM. Heat transfer in nozzles. Chemical Engineering Science. 1959;11(4):242–51.
21.
Saunders OA, Calder PH. Heat Transfer in a Nozzle at Supersonic Speeds. Proceedings of the Institution of Mechanical Engineers. 1953;167(1b):232–9.
22.
Schmucker R, Nasa, George C. Status of flow separation prediction in liquid propellant rocket nozzles, Technical Memorandum TM X-64890. 1974;
23.
Sommer TP, So RMC, Zhang HS. Near-wall variable-Prandtl-number turbulence model for compressible flows. AIAA Journal. 1993;31(1):27–35.
24.
Sommer T, So R, Zhang H. A Near Wall Four-Equation Turbulence model for Compressible Boundary Layers. 1994;
25.
Steger JL, Warming RF. Flux vector splitting of the inviscid gasdynamic equations with application to finite-difference methods. Journal of Computational Physics. 1981;40(2):263–93.
26.
Tong XL, Luke E. Turbulence Models and Heat Transfer in Nozzle Flows. AIAA Journal. 2004;42(11):2391–3.
27.
Vieser W, Esch T, Menter F. Heat Transfer Predictions Using Advanced Two-Equation Turbulence Models, CFX/ANSYS. 2002;
28.
Xiao X, Hassan HA, Edwards JR, Gaffney RL. Role of Turbulent Prandtl Numbers on Heat Flux at Hypersonic Mach Numbers. AIAA Journal. 2007;45(4):806–13.
The statements, opinions and data contained in the journal are solely those of the individual authors and contributors and not of the publisher and the editor(s). We stay neutral with regard to jurisdictional claims in published maps and institutional affiliations.
