Improved heat transfer prediction engineering capabilities for rocket thrust chamber layout

Maeding, C.; Wiedmann, D.; Quering, Katharina; Knab, O.

doi:10.1051/eucass/201102239

Cited by 7 publications

(6 citation statements)

References 2 publications

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“…On the one hand, the Nusselt-based engineering tool RCFS-II [2] is used mainly in the design process, delivering results within seconds of computational time. On the other hand, a more elaborate coupled CFDapproach is applied as soon as detailed analyses become necessary.…”

Section: Applied Toolsmentioning

confidence: 99%

“…The lower half of Fig. 2 presents the O/F ratio with fully separated hydrogen and Figure 3 Comparison of numerical simulation (Roc §am-II) (1) and test data for the 40-kilonewton combustor (minimal and maximal heat §ux) (2) oxygen near the faceplate and more and more mixing towards the throat and exit. Note the propellants do not mix perfectly until the throat, resulting in a combustion e©ciency below unity.…”

Section: Applied Toolsmentioning

confidence: 99%

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Consideration of real gas effects and condensation in a spray-combustion rocket-thrust-chamber design tool

Frey¹,

Kniesner²,

Knab³

2011

Progress in Propulsion Physics

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For the prediction of hot gas side heat transfer in rocket thrust chambers, Astrium Space Transportation (ST) uses the second generation multiphase Navier Stokes solver Roc §am-II. To account for real-gas and condensation e¨ects, pressure-dependent and even multiphase §uid data are included in the chemistry tables used by the code. Thus, the changing §uid properties near the two-phase region as well as transformation from gaseous to liquid and even solid state are re §ected properly. Heat §ux measurements for a dedicated subscale test campaign with strongly cooled walls show a clearly increasing heat load as soon as the combustion gases condense at the wall, due to the released latent heat of condensation. Corresponding coupled Roc §am-II/CFX simulations show a good quantitative agreement in heat §ux for load cases with and without condensation, showing the ability of the code to correctly simulate §ows in the real-gas and even inside the two-phase region.

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Section: Applied Toolsmentioning

confidence: 99%

Section: Applied Toolsmentioning

confidence: 99%

Consideration of real gas effects and condensation in a spray-combustion rocket-thrust-chamber design tool

Frey¹,

Kniesner²,

Knab³

2011

Progress in Propulsion Physics

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“…For early design validations of all three TCDs 2D axisymmetric CHT analyses have been performed. For this purpose Rocflam3 (in 2D/axisymmetric mode) has been coupled to RCFS-II, ArianeGroup's well-validated 1D in-house engineering tool for the coupled simulation of hot gas and coolant side heat transfer [14]. The initial design of all three TCDs was validated applying these tools [5,6].…”

Section: Design Validation Of the Tcdsmentioning

confidence: 99%

Definition and Evaluation of Advanced Rocket Thrust Chamber Demonstrator Concepts

Eiringhaus¹,

Riedmann²,

Knab³

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Since the beginning of the German collaborative research center SFB-TRR 40 in 2008 ArianeGroup has been involved as industrial partner and supported the research activities with its expertise. For the final funding period ArianeGroup actively contributes to the SFB-TRR 40 with the self-financed project K4. Within project K4 virtual thrust chamber demonstrators have been defined that allow the application of the attained knowledge of the entire collaborative research center to state-of-the-art numerical benchmark cases. Furthermore, ArianeGroup uses these testcases to continue the development of its in-house spray combustion and performance analysis tool Rocflam3. Unique within the collaborative research center fully three-dimensional conjugate heat transfer computations have been performed for a full-scale 100 kN upper stage thrust chamber. The strong three-dimensionality of the temperature field in the structure resulting from injection element and cooling channel configuration is displayed.

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“…All simulations were performed with a 12 species equilibrium chemistry superposed by a pdf-approach for modeling the turbulent GOX-kerosene combustion. The Rocflam-II simulations were coupled with the Astrium in house tool RCFS-II [4], which treats the heat conduction within the wall and the heat transfer into the coolant. Figure 3 compares the wall heat flux distribution from a Rocflam-II simulation to the test data obtained as heat load into the five chamber segments.…”

Section: Current State With All Improvementsmentioning

confidence: 99%

Simulation of a GOX–kerosene subscale rocket combustion chamber

Höglauer¹,

Kniesner²,

Knab³

et al. 2011

CEAS Space J

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In view of future film cooling tests at the Institute for Flight Propulsion (LFA) at Technische Universität München, the Astrium in-house spray combustion CFD tool Rocflam-II was validated against first test data gained from this rocket test bench without film cooling. The subscale rocket combustion chamber uses GOX and kerosene as propellants which are injected through a single double swirl element. Especially the modeling of the double swirl element and the measured wall roughness were adapted on the LFA hardware. Additionally, new liquid kerosene fluid properties were implemented and verified in Rocflam-II. Also the influences of soot deposition and hot gas radiation on the wall heat flux were analytically and numerically estimated. In context of reviewing the implemented evaporation model in Rocflam-II, the binary diffusion coefficient and its pressure dependency were analyzed. Finally simulations have been performed for different load points with Rocflam-II showing a good agreement compared to test data. List of symbolsTurbulent kinetic energy (m 2 /s 2 ) L Ã Characteristic length (m) _ m inj Injected mass flow (kg/s) _ m Total mass flow (kg/s) M Molar mass (kg/kmol) O/F Mixture ratio [-], O = F ¼ _ m Oxidizer _ m Fuel P c Chamber pressure (bar) _ Q int Integral heat load (kW) R a Mean roughness index (lm) T Temperature (K) V Volume of diffusion (-)

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Improved heat transfer prediction engineering capabilities for rocket thrust chamber layout

Cited by 7 publications

References 2 publications

Consideration of real gas effects and condensation in a spray-combustion rocket-thrust-chamber design tool

Consideration of real gas effects and condensation in a spray-combustion rocket-thrust-chamber design tool

Definition and Evaluation of Advanced Rocket Thrust Chamber Demonstrator Concepts

Simulation of a GOX–kerosene subscale rocket combustion chamber

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