Characterization of a Multi-Injector GOX/CH4 Combustion Chamber

Silvestri, Simona; Celano, M.P.; Schlieben, Gregor; Haidn, Oskar

doi:10.2514/6.2016-4992

Cited by 27 publications

(10 citation statements)

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“…The attention is focused, in particular, on injector-injector and injector-wall interaction. In order to have a first characterization of the injectors behavior, the multi-element combustion chamber is tested at low combustion chamber pressures and for a wide range of mixture ratios [23].…”

Section: Description Of the Test Casementioning

confidence: 99%

“…Within the framework of facilitating the development of CFD for rocket engines, several different configurations of rocket combustors and propellant combinations have been tested as part of the Transregio 40 as shown in Silvestri et al [23], building an experimental database which can be used in the validation process of CFD models. In this project, the accurate experimental determination of the heat loads and the numerical prediction of the wall heat transfer have a vital role.…”

Section: Introductionmentioning

confidence: 99%

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Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Perakis

Haidn

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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The experimental investigation of sub-scale rocket engines gives significant information about the combustion dynamics and wall heat transfer phenomena occurring in full-scale hardware. At the same time, the performed experiments serve as validation test cases for numerical CFD models and for that reason it is vital to obtain accurate experimental data. In the present work, an inverse method is developed able to accurately predict the axial and circumferential heat flux distribution in CH$$_4$$/O$$_2$$ rocket combustors. The obtained profiles are used to deduce information about the injector-injector and injector-flame interactions. Using a 3D CFD simulation of the combustion and heat transfer within a multi-element thrust chamber, the physical phenomena behind the measured heat flux profiles can be inferred. A very good qualitative and quantitative agreement between the experimental measurements and the numerical simulations is achieved.

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Section: Description Of the Test Casementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Perakis

Haidn

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

Self Cite

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“…Furthermore, the dimensions of the test chambers, e.g., the Pennstate pre-burner, were not really rocket-engine typical and therefore the results cannot be fully used as a blueprint for more application-relevant studies. Therefore, two new oxygen/methane combustion chamber test cases have been defined by the group of Prof. Haidn at the Technical University of Munich featuring more application-related chamber characteristics, e.g., element-element and element-wall distances: a single-element combustion chamber [4] and a 7-element combustor [25]. Using the single-element combustion chamber as a reference case, the influence of the turbulence wall model on the predicted wall heat flux has been investigated.…”

Section: Combustionmentioning

confidence: 99%

Numerical Investigation of Injection, Mixing and Combustion in Rocket Engines Under High-Pressure Conditions

Traxinger

Zips

Stemmer

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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The design and development of future rocket engines severely relies on accurate, efficient and robust numerical tools. Large-Eddy Simulation in combination with high-fidelity thermodynamics and combustion models is a promising candidate for the accurate prediction of the flow field and the investigation and understanding of the on-going processes during mixing and combustion. In the present work, a numerical framework is presented capable of predicting real-gas behavior and nonadiabatic combustion under conditions typically encountered in liquid rocket engines. Results of Large-Eddy Simulations are compared to experimental investigations. Overall, a good agreement is found making the introduced numerical tool suitable for the high-fidelity investigation of high-pressure mixing and combustion.

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“…In this framework, a wealth of experimental information has been recently obtained and made available to scientific community by a campaign of tests conceived and carried out at Technical University of Munich (TUM) [3][4][5][6]. Unfortunately, most of information is relevant to the combustion chamber.…”

Section: Introductionmentioning

confidence: 99%

“…Unfortunately, most of information is relevant to the combustion chamber. 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].…”

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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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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Characterization of a Multi-Injector GOX/CH4 Combustion Chamber

Cited by 27 publications

References 0 publications

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors

Numerical Investigation of Injection, Mixing and Combustion in Rocket Engines Under High-Pressure Conditions

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

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