PLIF Investigation of Reactive Flows in the Separation Region of an Over-Expanded Two-Dimensional Nozzle

Ordonneau, G.; Grisch, Frédéric; Vingert, Lucien; Hervat, Pierre; Reijasse, Philippe

doi:10.2514/6.2006-5209

Cited by 3 publications

(8 citation statements)

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“…The first results [3] obtained by PLIF visualizations performed in this test bench show an increase in concentrations of OH radical near the upper wall of the nozzle's divergent, in the separation zone. This suggests a reactivation of the combustion inside this area ( Figure 2).…”

Section: Objectivesmentioning

confidence: 87%

“…In these calculations the reduced chemical kinetic model of Eklund et al [4] was used for chemical rates. However no process of reignition in the flow has been pointed out from the numerical results [3].…”

Section: Objectivesmentioning

confidence: 92%

“…The authors related this phenomenon to the pressure fluctuations observed in the combustion chamber. An example of PLIF images obtained by this technique is depicted in Figure 2 [3]. However, no detailed explanations have been given so far about the occurrence of this phenomenon.…”

Section: Objectivesmentioning

confidence: 99%

“…Model. This reaction simplified scheme, proposed by Eklund et al [4] and implemented on both CEDRE and CPS codes, has been widely used by ONERA and CNES [3,20] Table 2, this scheme does not involve any third body reaction which can present an advantage in terms of computing time.…”

Section: Eklundmentioning

confidence: 99%

“…To understand these phenomena, a campaign of experimental measurements was conducted at the cryogenic LH 2 -LO 2 ONERA/Mascotte test bench facility [3]. The results yet obtained for low oxidizer/fuel ratios ( / ), on the basis of PLIF and Kulite pressure measurements, already constitute a very useful database for understanding the involved physicochemical phenomena.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling

Sellam¹,

Chpoun²

2015

International Journal of Aerospace Engineering

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Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at sea level or at low altitudes. Consequently, the induced wall thermal loads can lead to the nozzle geometry alteration, which in turn, leads to the appearance of strong side loads that may be detrimental to the rocket engine structural integrity. It is therefore necessary to understand both aerodynamic and chemical mechanisms that are at the origin of these processes. This paper is a numerical contribution which reports results from CFD analysis carried out for supersonic reactive flows in a planar nozzle cooled with GH2film. Like the experimental observations, CFD simulations showed their ability to highlight these phenomena for the same nozzle flow conditions. Induced thermal load are also analyzed in terms of cooling efficiency and the results already give an idea on their magnitude. It was also shown that slightly increasing the film injection pressure can avoid the reignition phenomena by moving the separation shock towards the nozzle exit section.

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Section: Objectivesmentioning

confidence: 87%

Section: Objectivesmentioning

confidence: 92%

Section: Objectivesmentioning

confidence: 99%

Section: Eklundmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling

Sellam¹,

Chpoun²

2015

International Journal of Aerospace Engineering

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Model-based active fault-tolerant control for a cryogenic combustion test bench

et al. 2020

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HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L'archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d'enseignement et de recherche français ou étrangers, des laboratoires publics ou privés.

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Automatic tuning strategies for model-based diagnosis methods applied to a rocket engine demonstrator

Iannetti¹,

Marzat

Piet-Lahanier

et al. 2016

PHME_CONF

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Rocket engines are complex and critical systems mostly relying on simple redlines strategies for monitoring the main functional parameters. This approach is typical on expendable rockets with non-adjustable valves because in case of failure the only possible action is to cut off the engine. Anyway years of experiments on engine firings or subsystem benches show that there is space for an update of the monitoring strategies because this would lead to a reduction of false alarm rates and to an improved exploitation of test hardware. Moreover real-time diagnosis methods will be necessary in case of design of intelligent rocket engine controllers for next generation reusable launchers. The work presented in this paper is part of a demonstration project of new diagnosis tools for rocket engines applied to the cryogenic combustion bench Mascotte. This bench developed by ONERA and CNES is used to analyze combustion and nozzle expansion characteristics of cryogenic fuels such as oxygen and hydrogen or methane. Model-based diagnosis tools have been developed for the combustion chamber and nozzle water cooling circuit. The basis was the setup of simplified expressions for modeling the functional behavior of the water circuit and then the development of predictive strategies such as parameter identification and Kalman filters. Anomalous event detection is obtained via residual analysis based on a CUSUM test. This paper presents the new automatic tuning strategies for the CUSUM threshold setting and the detection results obtained on Mascotte firing data.

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PLIF Investigation of Reactive Flows in the Separation Region of an Over-Expanded Two-Dimensional Nozzle

Cited by 3 publications

References 1 publication

Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling

Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling

Model-based active fault-tolerant control for a cryogenic combustion test bench

Automatic tuning strategies for model-based diagnosis methods applied to a rocket engine demonstrator

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