Heat Transfer Simulations in Liquid Rocket Engine Subscale Thrust Chambers

Negishi, Hideyo; Kumakawa, Akinaga; Yamanishi, Nobuhiro; Kurosu, Akihide

doi:10.2514/6.2008-5241

Cited by 15 publications

(12 citation statements)

References 2 publications

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“…7 a). The similar results show the numerical investigations for the region near to the injector head [ 4 ]. The non-uniformity of heat transport increase with the growing of combustion chamber pressure.…”

Section: Circumferential Distribution Of Thermal Loadssupporting

confidence: 85%

Investigation of Two Dimensional Thermal Loads in the Region Near the Injector Head of a High Pressure Subscale Combustion Chamber

Suslov

Arnold

Haidn

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Section: Circumferential Distribution Of Thermal Loadssupporting

confidence: 85%

Investigation of Two Dimensional Thermal Loads in the Region Near the Injector Head of a High Pressure Subscale Combustion Chamber

Suslov

Arnold

Haidn

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…14 illustrates the average heat flux along the thrust chamber in line 1 and line 2. A typical distribution of heat flux in thrust chamber is shown, which is consistent with the results shown in (Negishi et al, 2008) and (Oliver et al, 2009). In the cylindrical segment, the heat fluxes are little fluctuation with the axial distance ranges.…”

Section: Average Heat Flux and Wall Temperature In Different Work Timsupporting

confidence: 80%

Wall heat flux measurements in a GO<sub>2</sub>/GH<sub>2</sub> heat-sink combustion chamber

Wang

Sun

Xiang

et al. 2018

JTST

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In order to understand heat transfer mechanisms in the combustion chamber with multi-elements injector and provide benchmark data of wall heat fluxes for the CFD code validation, experiments were carried out in a GH2/GO2 heat-sink combustion chamber. To obtain the transient heat flux in the experiments, the LevenbergMarquardt method was modified and applied to the rocket combustion chamber based on the temperature measured by single coaxial thermocouple (Named "single-point method"). The comparison between the singlepoint method and the two-point method with temperatures measured in two points shows that the single-point method could be used as heat flux measurements of the heat-sink combustion chamber in engineering. Heat flux distribution was obtained in experimental conditions of different work time and chamber pressure by the modified method, feasibly and efficiently. For the transient variations of the heat flux, an inverse variation trend of heat flux to time in the cylindrical segment and the nozzle segment was observed. A typical variation of the averaged heat flux was obtained under the conditions with different chamber pressure and work time. The results of wall heat flux scaled with pressure to the power 0.8 can be uniformized for all pressure levels. The heat fluxes obtained in the cylindrical chamber and nozzle section may be applied for the life cycle prediction of rocket engines.

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“…14 The configuration and conditions of this reference experiment were described in a previous work. 14 The averaged heat flux distributions in the circumferential direction on the hotgas side wall are evaluated by the measured mass flow rate of the coolant water and the temperature gain in the cooling channels that are located at several axial locations. The hot-gas side wall temperature is also estimated using the averaged heat flux at the same locations by using a one-dimensional heat conduction analysis.…”

Section: B Test Case and Simplificationmentioning

confidence: 99%

Combustion and Heat Transfer Modeling in Regeneratively Cooled Thrust Chambers (Optimal Solution Procedures for Heat Flux Estimation of a Full-Scale Thrust Chamber)

Daimon¹,

Negishi²,

Yamanishi³

et al. 2012

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

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Combustion flowfields in GH2/LOX sub-scale calorimeter chambers with multi-injector elements and full-scale thrust chamber are investigated using Reynolds-Averaged NavierStokes simulation, in which the finite rate chemistry with the H 2 /O 2 detailed reaction mechanism is taken into account. The computed wall heat flux distributions are compared to that of the simplified cases to reduce a computational cost. The considered simplifications are a presence of reaction and a number of injector rows. At first, these simplifications are validated in the simulation of sub-scale chambers. The reaction is essential for the prediction of heat flux because it makes change the species distribution in a thermal boundary layer on a thrust chamber wall. A heat flux using a combustion simulation with only outermost injectors shows a good agreement with that with an original configuration near a face plate. On the other hand, it overestimates the heat flux around nozzle and throat parts. It is clarified that this overestimate comes from the shortage of unburned hydrogen near a chamber wall in the simplified method. Next, the simplification of the number of injector rows are applied to the simulation of full-scale thrust chambers. The effectiveness of this simplification for the prediction of wall heat flux is revealed. The optimal solution by using of the simplification is proven to be effective for the prediction of heat flux in a full-scale thrust chamber.

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Heat Transfer Simulations in Liquid Rocket Engine Subscale Thrust Chambers

Cited by 15 publications

References 2 publications

Investigation of Two Dimensional Thermal Loads in the Region Near the Injector Head of a High Pressure Subscale Combustion Chamber

Investigation of Two Dimensional Thermal Loads in the Region Near the Injector Head of a High Pressure Subscale Combustion Chamber

Wall heat flux measurements in a GO<sub>2</sub>/GH<sub>2</sub> heat-sink combustion chamber

Combustion and Heat Transfer Modeling in Regeneratively Cooled Thrust Chambers (Optimal Solution Procedures for Heat Flux Estimation of a Full-Scale Thrust Chamber)

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