Numerical Simulation of Liquid Rocket Engine Thrust Chamber Regenerative Cooling

Kang, Ying-Wei; Sun, Bing

doi:10.2514/1.47701

Cited by 43 publications

(16 citation statements)

References 15 publications

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“…Most investigations implemented coupled heat transfer to simulate asymmetrically heated cooling channels because the temperature fields of the fluid region obtained with and without wall heat conduction are significantly different [2]. Previous studies showed that the selected geometries, fluids (hydrogen, nitrogen, methane), and boundary conditions were close to those expected in the regenerative cooling system of rocket engines (Froelich et al [3], Neuner et al [4], Jung et al [5], DiValentin and Naraghi [6], Kang and Sun [7], Pizzarelli et al [2,[8][9][10][11][12][13][14], Negishi et al [15], Ruan and Meng [16], and Wang et al [17]). A high aspect ratio cooling channel (HARCC) has been widely used in the regenerative cooling system of rocket engines.…”

Section: Introductionmentioning

confidence: 92%

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Coupled Heat Transfer of Supercritical n-Decane in a Curved Cooling Channel

Liang

Liu

Pan

2016

Journal of Thermophysics and Heat Transfer

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The coupled heat transfer of supercritical-pressure n-decane in a concave heated, 90 deg bend, square channel was investigated numerically. Both the geometry and boundary conditions were close to those expected in active-cooled scramjet engines. The effect of secondary motions and wall thermal conductivity on heat transfer was studied. The flowfields obtained by the Spalart-Allmaras model and Reynolds stress model were compared. The secondary flow of Prandtl's first kind caused by the crosswise pressure gradient in the curved section was 1.0% of the maximum axial velocity. The secondary flow of Prandtl's second kind caused by Reynolds stress was one magnitude less than that of Prandtl's first kind. The Spalart-Allmaras turbulence model produced reasonable results with less computational effort than the Reynolds stress model. Secondary flow improves heat transfer by enhancing the mixing of the fluid. Furthermore, higher wall thermal conductivity produces more uniformly distributed temperature and heat flux. Nomenclature c p = specific heat at constant pressure, J · kg −1 K −1 D h = hydraulic diameter of cooling channel, m G = mass flux, kg · m −2 s −1 k w = wall thermal conductivity, W·m −1 K −1 P = pressure, Pa R = radii of curved channel, m q w = heat flux, W·m −2 T = temperature, K u x , u y = x, y velocity component of secondary flow, ms −1 u z = axial velocity, m·s −1 u z0 = axial velocity at centerline of channel, m·s −1 ρ = density, kg · m −3

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Section: Introductionmentioning

confidence: 92%

“…The secondary flow of Prandtl's second kind can also be captured by the Reynolds stress model (RSM). Kang and Sun [7] adopted the RSM in the simulation of a liquid rocket engine thrust chamber but did not focus on the detailed flowfield in cooling channels. A curved cooling channel with high aspect ratio in the upper part of Fig.…”

Section: Introductionmentioning

confidence: 99%

Coupled Heat Transfer of Supercritical n-Decane in a Curved Cooling Channel

Liang

Liu

Pan

2016

Journal of Thermophysics and Heat Transfer

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“…Recently, coupled CFD analysis for the whole regeneratively-cooled thrust chamber has been performed. 13,14 All of these approaches have their well-defined objective that in some cases lead to fast and simplified methods and in other cases to heavy computations which are not suited to engine design phase.…”

Section: Introductionmentioning

confidence: 99%

Coupled Heat Transfer Analysis in Regeneratively Cooled Thrust Chambers

Betti¹,

Pizzarelli²,

Nasuti³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A computational procedure able to describe the coupled hot-gas/wall/coolant environment that occurs in most liquid rocket engines and to provide a quick and reliable prediction of thrust-chamber wall temperature and heat flux as well as coolant-flow characteristics, like pressure drop and temperature gain in the regenerative circuit is presented and demonstrated. The coupled analysis is performed by means of an accurate CFD solver of the Reynolds-Averaged Navier-Stokes equations for the hot-gas flow and a simplified quasi-2D approach, which widely relies on semi-empirical relations, to study the problem of coolant flow and wall structure heat transfer in the cooling channels. Coupled computations of the Space Shuttle Main Engine Main Combustion Chamber are performed and compared with available literature data. Results show a reasonable agreement in terms of coolant pressure drop and temperature gain with nominal data, whereas the computed wall temperature peak is quite closer to hot-firing data than to the nominal value. © 2012 by B. Betti, M. Pizzarelli, F. Nasuti

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“…[18][19][20][21][22][23][24] Recently, as the computational resources increase, coupled CFD analyses for the whole regeneratively-cooled thrust chamber are also performed. [25][26][27] Objective of the present work is to describe the coupled hot-gas/wall/coolant environment of the HYPROB program engine demonstrator with particular interest to the regenerative cooling performances. In particular, this study is performed by means of a Conjugate Heat Transfer (CHT) model based on the coupled numerical integration of the three-dimensional Navier-Stokes Equations for the coolant flow and Fourier's Equation for the heat conduction in the solid material.…”

Section: Introductionmentioning

confidence: 99%

Cooling Channel Analysis of a LOX/LCH4 Rocket Engine Demonstrator

Pizzarelli¹,

Betti

Nasuti

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A computational procedure able to describe the coupled hot-gas/wall/coolant environment that occurs in most liquid rocket engines is presented and demonstrated. The coupled analysis is performed by loose coupling of the two-dimensional axisymmetric Reynolds-Averaged Navier-Stokes equations for the hot-gas flow and the conjugate three-dimensional model for the coolant flow and solid material heat transfer in the regenerative cooling circuit. The latter model is in turn based on the coupled Reynolds-Averaged Navier-Stokes equations for the coolant flow and Fourier equation for the thermal conduction in the solid material. In this study, the thermal behavior of a regeneratively cooled oxygen/methane engine demonstrator is analyzed in detail. Starting from a nominal operative condition of the engine, different levels of channel surface roughness and coolant mass flow rate are considered in order to understand their influence on the heat transfer capability of the cooling system. Results show that the heat transfer can be markedly impaired if the operating parameters undergo rather minor changes with respect to the nominal condition

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Numerical Simulation of Liquid Rocket Engine Thrust Chamber Regenerative Cooling

Cited by 43 publications

References 15 publications

Coupled Heat Transfer of Supercritical n-Decane in a Curved Cooling Channel

Coupled Heat Transfer of Supercritical n-Decane in a Curved Cooling Channel

Coupled Heat Transfer Analysis in Regeneratively Cooled Thrust Chambers

Cooling Channel Analysis of a LOX/LCH4 Rocket Engine Demonstrator

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