Numerical Investigations of Heat Transfer Enhancement in a Thrust Chamber with Hot Gas Side Wall Ribs

Negishi, Hideyo; Kumakawa, Akinaga; Moriya, Shinichi; Yamanishi, Nobuhiro; Sunakawa, Hideo

doi:10.2514/6.2009-830

Cited by 6 publications

(7 citation statements)

References 2 publications

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“…In this section, heat fluxes obtained with the CHT-LES for both configurations are compared to heat transfer measurements from the experiments as well as with RANS results published by JAXA [ 11 ]. Time-averaged wall heat fluxes of ribbed and smooth configurations are plotted along the axial direction of the combustion chamber on Figure 22 .…”

Section: Resultsmentioning

confidence: 99%

“…The global evolution of the heat flux along the axis is recovered in both simulations, and fluxes are under-estimated by ≈10–20% compared to experimental measurements. RANS-published simulation [ 11 ] was conducted with a droplet injection model fitted to match heat flux measurement for the smooth chamber. However, the results of the ribbed configuration show under-predicted heat flux in the middle of the chamber and over-predicted heat-flux at the end.…”

Section: Resultsmentioning

confidence: 99%

“…The main geometrical features are summarized in Table 1 . Other details about geometry and experiments can be found in [ 11 ]. Chamber walls in the cylindrical section are about 1 cm thick.…”

Section: The Jaxa Chamber Configurationsmentioning

confidence: 99%

“…The JAXA (Japan Aerospace Exploration Agency) also experimentally studied heat flux enhancement using ribbed walls [ 10 , 11 ] with two experimental thrust chambers: one with smooth walls and the other with ribbed walls. The two chambers have been designed to operate with

but only at one targeted pressure and mixture ratio.…”

Section: Introductionmentioning

confidence: 99%

“…Large Eddy Simulation (LES) allows one to describe most of these phenomena and their interaction in an unsteady context producing better results than RANS approaches. The objective of this paper is to investigate numerically, thanks to LES, the heat transfer enhancement on the JAXA ribbed configurations compared to the smooth case [ 10 , 11 ] with state-of-the-art methods for turbulent reactive flows including liquid injection, combustion kinetics, wall treatment, and Conjugate Heat Transfer (CHT). The LES code AVBP (Advanced Virtual Burner Program) developed by CERFACS has already proven its ability to reproduce combustion in representative rocket engine conditions [ 14 , 15 , 16 , 17 , 18 , 19 ] in transcritical and supercritical regimes as well as for subcritical regimes [ 20 ] and for transient ignition [ 21 ].…”

Section: Introductionmentioning

confidence: 99%

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Although a lot of research and development has been done to understand and master the major physics involved in cryogenic rocket engines (combustion, feeding systems, heat transfer, stability, efficiency, etc.), the injection system and wall heat transfer remain critical issues due to complex physics, leading to atomization in the subcritical regime and the interactions of hot gases with walls. In such regimes, the fuel is usually injected through a coaxial annulus and triggers the atomization of the central liquid oxidizer jet. This type of injector is often referred to as air-assisted, or coaxial shear, injector, and has been extensively studied experimentally. Including such injection in numerical simulations requires specific models as simulating the atomization process is still out of reach in practical industrial systems. The effect of the injection model on the flame stabilization process and thus on wall heat fluxes is of critical importance when it comes to the design of wall-cooling systems. Indeed, maximizing the heat flux extracted from the chamber can lead to serious gain for the cooling and feeding systems for expander-type feeding cycles where the thermal energy absorbed by the coolant is converted into kinetic energy to drive the turbo-pumps of the feeding system. The methodology proposed in this work to numerically predict the flame topology and associated heat fluxes is based on state-of-the-art methods for turbulent reactive flow field predictions for rocket engines, including liquid injection, combustion model, and wall treatment. For this purpose, high-fidelity Large Eddy Simulation Conjugate Heat Transfer, along with a reduced kinetic mechanism for the prediction of H2/O2 chemistry, liquid injection model LOx sprays, and the use of a specific wall modeling to correctly predict heat flux for large temperature ratio between the bulk flow and the chamber walls, is used. A smooth and a longitudinally ribbed combustor configuration from JAXA are simulated. The coupling strategy ensures a rapid convergence for a limited additional cost compared to a fluid-only simulation, and the wall heat fluxes display a healthy trend compared to the experimental measurements. An increase of heat transfer coherent with the literature is observed when walls are equipped with ribs, compared to smooth walls. The heat transfer enhancement of the ribbed configuration with respect to the smooth walls is coherent with results from the literature, with an increase of around +80% of wall heat flux extracted for the same chamber diameter.

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Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

Section: The Jaxa Chamber Configurationsmentioning

confidence: 99%

but only at one targeted pressure and mixture ratio.…”

Section: Introductionmentioning

confidence: 99%