Qualitative and Quantitative Comparison of RANS Simulation Results for a 7-Element GOX/GCH4 Rocket Combustor

Perakis, Nikolaos; Haidn, Oskar; Eiringhaus, Daniel; Rahn, Daniel; Zhang, Silong; Daimon, Yu; Karl, Sebastian; Horchler, Tim

doi:10.2514/6.2018-4556

Cited by 30 publications

(31 citation statements)

References 5 publications

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“…Fig. 7 Computed (Sapienza) and experimental [11] heat flux at each segment Fig. 8 Computed (Sapienza) and corrected experimental [11] heat flux at each segment…”

Section: Resultsmentioning

confidence: 99%

“…However, results of a new test including the measure of coolant temperature increase in throat region have been made recently available [5,6]. These data have been considered a testbench for code validation by different Dipartimento di Ingegneria Meccanica ed Aerospaziale, "La Sapienza"-Università di Roma, Rome, Italy research groups making use of both commercial and inhouse CFD software [7][8][9][10][11][12][13][14][15]. In this paper, some aspects of modeling are deepened to get more insight on the driving phenomena for the correct prediction of throat heat flux.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

Concio

Migliorino

Nasuti

2020

Aerotec. Missili Spaz.

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The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challenge, because of the little experimental information. Such a problem is of obvious importance in general, and becomes even more important when considering reusable engines. Unfortunately, only few indirect experimental data are available for the validation of throat heat flux prediction. On the numerical side, a detailed solution would require a huge resolution and codes able to solve at the same time combustion, boundary layer with possible finite-rate reactions, expansion up to at least sonic speed, and in some cases radiative heat flux. Therefore, it is important to validate, with the few experimental data available in the literature, simplified CFD approaches whose aim is to predict heat flux in the nozzle in affordable times. Results obtained by different numerical models based on a RANS approach show the correctness and quality of the approximations made, indicating the main phenomena to be included in modeling for the correct prediction of throat heat flux.

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“…Fig. 7 Computed (Sapienza) and experimental [11] heat flux at each segment Fig. 8 Computed (Sapienza) and corrected experimental [11] heat flux at each segment…”

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

Concio

Migliorino

Nasuti

2020

Aerotec. Missili Spaz.

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“…Within the SFB-TRR 40 projects K1 and C1/C6 have been working on different combustion models based on non-adiabatic flamelets. A benchmarking of different modeling strategies of groups from the SFB-TRR 40 as well as additional groups from DLR, Jaxa and the University of Harbin has been performed in the frame of the summer program 2017 and published [16]. A detailed combustion analysis of demonstrator TCD3 has been performed within project C1/C6 [25].…”

Section: Tcd3-overview and Cooperationmentioning

confidence: 99%

Definition and Evaluation of Advanced Rocket Thrust Chamber Demonstrator Concepts

Eiringhaus¹,

Riedmann²,

Knab³

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

Self Cite

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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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“…One example is the seven injector gaseous combustor of the TU Munich which was considered by many numerical groups around the world (see, e.g. the review paper of Periakis et al [8]). However, this test case is limited to gaseous fuels and requires the simulation of a full combustion chamber with limited experimental data for comparison.…”

Section: Introductionmentioning

confidence: 99%

Proceedings of the 3rd International Seminar on Non-Ideal Compressible Fluid Dynamics for Propulsion and Power

Pini¹,

Servi²,

Spinelli³

et al. 2021

ERCOFTAC Series

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The accurate numerical simulation of high-pressure rocket combustion chambers is a key element for the design of future space transportation vehicles. In recent years investigations focus more and more on methane-based combustion chambers for which many thermodynamic and combustion issues are still unknown. Experimental investigations indicate that we might have to deal with a close interaction of nonideal equation-of-state effects together with complex kinetic schemes.On the numerical side the main challenges include the consistent approximation of thermodynamic effects within a broad temperature range from cryogenic injection up to high temperature effects at combustion. Nowadays simple numerical test cases are missing to study and understand the basic effects during the injection and combustion process, especially with methane as propellant. This open question is addressed by the definition of a simple test case for cryogenic methane combustion and its analysis by applying a range of thermodynamic and kinetic models.

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Qualitative and Quantitative Comparison of RANS Simulation Results for a 7-Element GOX/GCH4 Rocket Combustor

Cited by 30 publications

References 5 publications

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

Definition and Evaluation of Advanced Rocket Thrust Chamber Demonstrator Concepts

Proceedings of the 3rd International Seminar on Non-Ideal Compressible Fluid Dynamics for Propulsion and Power

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