Heat transfer modeling for supercritical methane flowing in rocket engine cooling channels

Pizzarelli, Marco; Nasuti, Francesco; Onofri, Marcello; Roncioni, Pietro; Votta, Raffaele; Battista, Francesco

doi:10.1016/j.applthermaleng.2014.10.008

Cited by 51 publications

(10 citation statements)

References 16 publications

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“…Email: josetkm@tkmce.ac.in which takes into account thermal stratification. Pizzarelli et al (2007Pizzarelli et al ( , 2008Pizzarelli et al ( , 2009aPizzarelli et al ( , 2009bPizzarelli et al ( , 2010Pizzarelli et al ( , 2011Pizzarelli et al ( , 2012Pizzarelli et al ( , 2013aPizzarelli et al ( , 2013bPizzarelli et al ( , 2014Pizzarelli et al ( , 2015 conducted a number of numerical studies to predict coolant flow and heat transfer deterioration in coolant channels with cryogenic methane as the fluid. They developed a simplified model to evaluate the thermal stratification in solid fin as well as the coolant.…”

Section: Introductionmentioning

confidence: 99%

Effect of Aspect Ratio on Supercritical Heat Transfer of Cryogenic Methane in Rocket Engine Cooling Channels

Arun¹,

Akhil²,

Noufal³

et al. 2017

Frontiers in Heat and Mass Transfer

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The supercritical turbulent flow of cryogenic methane flowing in a rocket engine cooing channel is numerically analysed by imposing constant heat flux at the bottom surface of the channel. The calculation scheme is validated by comparing the results obtained with experimental results reported in literature. The heat transfer coefficient is influenced by the strong variation in thermophysical properties of methane at super critical pressure. An increasing trend in the average value of Nusselt number is observed with aspect ratio. The efficacy of both Modified Jackson and Hall and Bishop empirical correlations in predicting Nusselt number is tested for cryogenic methane flowing in coolant channels.

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Section: Introductionmentioning

confidence: 99%

Effect of Aspect Ratio on Supercritical Heat Transfer of Cryogenic Methane in Rocket Engine Cooling Channels

Arun¹,

Akhil²,

Noufal³

et al. 2017

Frontiers in Heat and Mass Transfer

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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: 91%

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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“…Most research works have focused on the effects of the operation conditions such as heat flux, mass flow rate, operating pressure and initial temperature on the irregular heat transfer [11][12][13][14]. In addition, studies of the buoyancy force and thermal-induced acceleration have also appeared to reveal the mechanism of the HTD [15][16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis of supercritical n-decane upward flow and heat transfer characteristics in the buffer layer of a vertical tube

Sun

Xie

et al. 2019

Numerical Heat Transfer, Part A: Applications

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To explore the behavior and mechanisms of heat transfer deterioration (HTD), the flow and thermal performances of supercritical n-decane in upward vertical tubes are investigated with emphasis on the boundary layer. It is realized that the dramatic variation of the thermophysical properties can cause unconventional heat transfer phenomenon and the change of the density is important in particular. The intensity of the HTD gradually increases once the position of the pseudo-critical temperature lays in the buffer layer region. Correspondingly, the turbulence kinetic energy is significantly suppressed. The large temperature gradient in the buffer layer zone means that the temperature commonly used in existing empirical correlations and based on the wall temperature or bulk temperature is not very appropriate and such an approach leads to poor prediction accuracy of the correlations.

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Heat transfer modeling for supercritical methane flowing in rocket engine cooling channels

Cited by 51 publications

References 16 publications

Effect of Aspect Ratio on Supercritical Heat Transfer of Cryogenic Methane in Rocket Engine Cooling Channels

Effect of Aspect Ratio on Supercritical Heat Transfer of Cryogenic Methane in Rocket Engine Cooling Channels

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

Numerical analysis of supercritical n-decane upward flow and heat transfer characteristics in the buffer layer of a vertical tube

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