Injector-Driven Combustion Instabilities in a Hydrogen/Oxygen Rocket Combustor

Gröning, Stefan; Hardi, Justin; Suslov, Dmitry; Oschwald, Michael

doi:10.2514/1.b35768

Cited by 106 publications

(92 citation statements)

References 54 publications

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“…There is however new information in this field. First, it appears that the transverse mode in the chamber is coupled with a longitudinal mode of the oxygen injectors, which is supported by the experimental findings of [36] . The associated structure resembles that of a 3/2-wave mode.…”

Section: Power Spectral Density Fieldsmentioning

confidence: 56%

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Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Urbano

Selle

Staffelbach

et al. 2016

Combustion and Flame

177

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et al.. Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector Liquid Rocket Engine. Combustion and Flame, Elsevier, 2016, 169, pp. a b s t r a c tThis article explores the possibility of analyzing combustion instabilities in liquid rocket engines by making use of Large Eddy Simulations (LES). Calculations are carried out for a complete small-scale rocket engine, including the injection manifold thrust chamber and nozzle outlet. The engine comprises 42 coaxial injectors feeding the combustion chamber with gaseous hydrogen and liquid oxygen and it operates at supercritical pressures with a maximum thermal power of 80 MW. The objective of the study is to predict the occurrence of transverse high-frequency combustion instabilities by comparing two operating points featuring different levels of acoustic activity. The LES compares favorably with the experiment for the stable load point and exhibits a nonlinearly unstable transverse mode for the experimentally unstable operating condition. A detailed analysis of the instability retrieves the experimental data in terms of spectral features. It is also found that modifications of the flame structures and of the global combustion region configuration have similarities with those observed in recent model scale experiments. It is shown that the overall acoustic activity mainly results from the combination of one transverse and one radial mode of the chamber, which are also strongly coupled with the oxidizer injectors.

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Section: Power Spectral Density Fieldsmentioning

confidence: 56%

“…The study considers an experimental thrust chamber designated as the BKD comprising a large number of injectors and operated at the P8 test facility at DLR Lampoldshausen [28,29,36] . Self-excited combustion instabilities (CI) develop for selected load points at frequencies corresponding to the transverse acoustic modes of the chamber.…”

Section: Introductionmentioning

confidence: 99%

Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Urbano

Selle

Staffelbach

et al. 2016

Combustion and Flame

177

View full text Add to dashboard Cite

show abstract

“…The propellants are oxygen and hydrogen and the BKD is typically operated in the transcritical regime where liquid oxygen at subcritical temperature enters the chamber that is at supercritical pressure. A description of the apparatus can be found in the work of Gröning et al [22][23][24] . The operating conditions correspond to an unstable load point referred to as LP4 for which the pressure chamber is p c = 80 bar and the thermal power assuming complete combustion is around 86 MW.…”

Section: Configuration and Les Datasetmentioning

confidence: 99%

Study of flame response to transverse acoustic modes from the LES of a 42-injector rocket engine

Urbano

Douasbin

Selle

et al. 2017

Proceedings of the Combustion Institute

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“…For high-performance power generation and propulsion systems, such as those of airbreathing and rocket engines, physical experiments are extremely expensive due to the harsh requirements of operating conditions and high level of system complexities [1][2][3]. In addition, it is difficult to gain insight into the underlying mechanisms of the physiochemical processes involved because of the typical reliance upon optical diagnostics for experimental measurements [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Common Proper Orthogonal Decomposition-Based Spatiotemporal Emulator for Design Exploration

et al. 2018

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The present study proposes a data-driven framework trained with high-fidelity simulation results to facilitate decision making for combustor designs. At its core is a surrogate model employing a machine-learning technique called kriging, which is combined with data-driven basis functions to extract and model the underlying coherent structures. This emulation framework encompasses key design parameter sensitivity analysis, physics-guided classification of design parameter sets, and flow evolution modeling for efficient design survey. To better inform the model of quantifiable physical knowledge, a sensitivity analysis using Sobol' indices and a decision tree are incorporated into the framework. This information improves the surrogate model training process, which employs basis functions as regression functions over the design space for the kriging model. The novelty of the proposed approach is the construction of the model through Common Proper Orthogonal Decomposition, which allows for data-reduction and extraction of common coherent structures. The accuracy of prediction of mean flow features for new swirl injector designs is assessed and the dynamic flowfield is captured in the form of power spectrum densities. This data-driven framework also demonstrates the uncertainty quantification of predictions, 2 providing a metric for model fit. The significantly reduced computation time required for evaluating new design points enables efficient survey of the design space.

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Injector-Driven Combustion Instabilities in a Hydrogen/Oxygen Rocket Combustor

Cited by 106 publications

References 54 publications

Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Study of flame response to transverse acoustic modes from the LES of a 42-injector rocket engine

Common Proper Orthogonal Decomposition-Based Spatiotemporal Emulator for Design Exploration

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