Heat Transfer and Combustion Simulation of Seven-Element O2/CH4 Rocket Combustor

Perakis, Nikolaos; Rahn, Daniel; Haidn, Oskar; Eiringhaus, Daniel

doi:10.2514/1.b37402

Cited by 31 publications

(37 citation statements)

References 30 publications

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“…Here an elongated flame shape can be recognized. Numerical investigations [17] in a sub-scale combustion chamber show a similar behavior of Menter's SST model whereas simulations with a k − ε turbulence model led to flames of uniform length. The authors explain the increased flame length of the SST model with a reduced mixing due to decreased turbulence production in the area of active k − ω model.…”

Section: D Conjugate Heat Transfer Investigation Of Tcd1mentioning

confidence: 63%

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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Section: D Conjugate Heat Transfer Investigation Of Tcd1mentioning

confidence: 63%

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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“…The black cells represent the post-tip between oxygen and fuel and the red and blue cells the CH 4 and O 2 inlets respectively. The grid is chosen after a grid convergence study, which is shown in [20].…”

Section: Computational Setupmentioning

confidence: 99%

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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“…21 Near-injector flame of a gas/gas (left) and gas/liquid (right) CH4/O2 Combustor Fig. 22 Instantaneous temperature distribution for the PennState model combustor using iDDES ments [52,53]. Recently, the facility, a single injector combustor and the 7-injector element combustor were modified to allow for operation with liquid oxygen, too.…”

Section: Combustion and Heat Transfermentioning

confidence: 99%

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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Heat Transfer and Combustion Simulation of Seven-Element O2/CH4 Rocket Combustor

Cited by 31 publications

References 30 publications

Definition and Evaluation of Advanced Rocket Thrust Chamber Demonstrator Concepts

Definition and Evaluation of Advanced Rocket Thrust Chamber Demonstrator Concepts

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

Collaborative Research for Future Space Transportation Systems

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