Gaseous Film Cooling Investigation in a Model Single Element GCH4-GOX Combustion Chamber

Celano, M.P.; Silvestri, Simona; Kirchberger, Christoph; Schlieben, Gregor; Suslov, Dmitry; Haidn, Oskar

doi:10.2322/tastj.14.pa_129

Cited by 7 publications

(10 citation statements)

References 5 publications

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“…Flamelet tables have been generated in a pre-processing phase taking into account the influence of non-adiabatic sources and turbulent fluctuations since the conventional adiabatic models are not able to capture the recombination phenomena in proximity of the cooled chamber walls. Large-Eddy Simulations with and without film cooling have been performed, achieving good agreement for the wall heat flux with the experimental data [34]. The heat flux is decreased by the cooling film, the full mixing of fuel and oxidizer is reached in the same position in the axial direction as for the non-cooled case.…”

Section: Boundary Layer Heat Transfer Modellingmentioning

confidence: 66%

Collaborative Research for Future Space Transportation Systems

Haidn

Adams

Radespiel

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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This chapter book summarizes the major achievements of the five topical focus areas, Structural Cooling, Aft-Body Flows, Combustion Chamber, Thrust Nozzle, and Thrust-Chamber Assembly of the Collaborative Research Center (Sonderforschungsbereich) Transregio 40. Obviously, only sample highlights of each of the more than twenty individual projects can be given here and thus the interested reader is invited to read their reports which again are only a summary of the entire achievements and much more information can be found in the referenced publications. The structural cooling focus area included results from experimental as well as numerical research on transpiration cooling of thrust chamber structures as well as film cooling supersonic nozzles. The topics of the aft-body flow group reached from studies of classical flow separation to interaction of rocket plumes with nozzle structures for sub-, trans-, and supersonic conditions both experimentally and numerically. Combustion instabilities, boundary layer heat transfer, injection, mixing and combustion under real gas conditions and in particular the investigation of the impact of trans-critical conditions on propellant jet disintegration and the behavior under trans-critical conditions were the subjects dealt with in the combustion chamber focus area. The thrust nozzle group worked on thermal barrier coatings and life prediction methods, investigated cooling channel flows and paid special attention to the clarification and description of fluid-structure-interaction phenomena I nozzle flows. The main emphasis of the focal area thrust-chamber assembly was combustion and heat transfer investigated in various model combustors, on dual-bell nozzle phenomena and on the definition and design of three demonstrations for which the individual projects have contributed according to their research field.

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Section: Boundary Layer Heat Transfer Modellingmentioning

confidence: 66%

Collaborative Research for Future Space Transportation Systems

Haidn

Adams

Radespiel

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…For this work two different CFD codes were used, CATUM [6] and OpenFOAM 1 , in order to compare the performance of the two and assess advantages and disadvantages of a pressure-based (OpenFOAM) against a density-based (CATUM) solver in combustion chamber environments.…”

Section: Governing Equations and Numerical Proceduresmentioning

confidence: 99%

“…The study of the wall heat transfer in a combustion chamber represents one of the most relevant design criteria of a modern launcher engine. Peak temperatures up to 3500 K and heat fluxes up to 160 MW/m 2 endanger the structural integrity of the engine, such that an efficient cooling system is necessary [1]. Normally, multiple cooling systems are employed simultaneously, but in this work the film cooling technique is investigated.…”

Section: Introductionmentioning

confidence: 99%

“…The authors show a realistic growth of the thermal boundary layer, but did not manage to match the experimental data. In this work, Large-Eddy Simulations are performed using a non-adiabatic Flamelet approach, in order to validate the combustion model against the experimental data of a single-injector combustion chamber [1]. A setup with and without film cooling is used, while the wall heat flux prediction is compared to the experiment.…”

Section: Introductionmentioning

confidence: 99%

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Large-Eddy Simulations for the Wall Heat Flux Prediction of a Film-Cooled Single-Element Combustion Chamber

Olmeda

Breda

Stemmer

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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In order for modern launcher engines to work at their optimum, film cooling can be used to preserve the structural integrity of the combustion chamber. The analysis of this cooling system by means of CFD is complex due to the extreme physical conditions and effects like turbulent fluctuations damping and recombination processes in the boundary layer which locally change the transport properties of the fluid. The combustion phenomena are modeled by means of Flamelet tables taking into account the enthalpy loss in the proximity of the chamber walls. In this work, Large-Eddy Simulations of a single-element combustion chamber experimentally investigated at the Technical University of Munich are carried out at cooled and non-cooled conditions. Compared with the experiment, the LES shows improved results with respect to RANS simulations published. The influence of wall roughness on the wall heat flux is also studied, as it plays an important role for the lifespan of a rocket engine combustors.

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“…GOX and GCH4 are injected via a coaxial injector at respectively 278K and 269K, with mass flow rates of 45 g/s and 17 g/s. Since the flamelets will be further validated in a configuration with film cooling [17] the computational domain was shortened from the original 303mm to 150mm, in order to investigate the near-injector region. Temperature distributions are available from thermocouples readings, which allow for a comparison of the wall heat flux.…”

Section: Turbulent Flamementioning

confidence: 99%

A Non-Adiabatic Flamelet Approach for Non-Premixed O2-CH4 Combustion

Breda¹,

Zips²,

Pfitzner³

2018

Proceedings of the 3rd World Congress on Momentum, Heat and Mass Transfer

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Numerical simulations of turbulent reactive flows are challenging due to the stiffness of chemical rate equations, depending on the number of species, reactions and time scales involved. A possible solution to speed-up the calculations is the use of tabulated manifolds for the thermo-chemical properties of the flame. In order to capture the effects of the flame-wall interactions, the pre-processed library shall include a parameter which accounts for heat losses. The generation of a non-adiabatic flamelet manifold is presented in this work, where the enthalpy defect experienced in proximity of the wall is included in the flamelet generation. A laminar simulation of a non-premixed methane/oxygen flame at elevated pressure is run to validate the manifold. The main differences to the frozen chemistry tabulation method previously in use are then underlined and referred to a finite rate chemistry case. Finally, a first assessment of the models was performed, based on a single-injector rocket chamber test case. The wall heat flux is compared with the available experimental results.

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Gaseous Film Cooling Investigation in a Model Single Element GCH4-GOX Combustion Chamber

Cited by 7 publications

References 5 publications

Collaborative Research for Future Space Transportation Systems

Collaborative Research for Future Space Transportation Systems

Large-Eddy Simulations for the Wall Heat Flux Prediction of a Film-Cooled Single-Element Combustion Chamber

A Non-Adiabatic Flamelet Approach for Non-Premixed O2-CH4 Combustion

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