Flow instabilities and acoustic resonance of channels with wall injection

Avalon, G.; Casalis, Grégoire; Griffond, Jérôme

doi:10.2514/6.1998-3218

Cited by 63 publications

(41 citation statements)

References 6 publications

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“…Fig.4.4 shows the computational results with the laminar flow and Magali's computational result (Magali, 2006), and both the computational results are well matched. The experiment results (Avalon et al, 1998;Yumusak et al, 2006) are also plotted in Fig. 4.4.…”

Section: Vecla Modelmentioning

confidence: 99%

“…The injected flow is exhausted from the simplified nozzle. On the other hand, ONERA also conducted the experiment of VECLA model to investigate the structure of VSP (Vortex Shedding Perion) in the SRM combustion chamber (Avalon et al, 1998;Yumusak et al, 2006). Similar but different experimental setup is built for the model as shown in Fig.…”

Section: Methods 21 Taylor Flow Modelmentioning

confidence: 99%

“…Fig. 4.5 shows the experiment results (Avalon et al, 1998;Yumusak et al, 2006) where laminar-turbulence transition is occurred. The normalized velocity is plotted, which is based on an average velocity (Um) at each location.…”

Section: Vecla Modelmentioning

confidence: 99%

“…The precise contents of analysis are Taylor Flow model (VALDO model (Cerqueria et al, 2009) and VECLA model (Avalon et al, 1998)), CDV (Converging-Diverging Verification) nozzle and Simple SRM model. All models are used to validate the flowfiled for each component part of SRM combustion chamber.…”

Section: Introductionmentioning

confidence: 99%

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Two-dimensional computational fluid dynamics analysis of internal flow in a simplified solid rocket motor combustion chamber

Ogawa

Sasaki

2017

JFST

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Many countries in recent year have focused on small satellite launch. Therefore, Solid Rocket Motor (SRM) plays an important role in the development of small satellites. However, vortical flows sometimes occur from an inhibitor in the propellant, which causes the pressure oscillation. The basic research was carried out to compute various types of simplified SRM model. In this study, Cartesian mesh-based CFD solver, Building-Cube Method (BCM), was employed with the implementation of internal flow boundary condition, and applied for two Taylor Flow models, CDV nozzle and Simple SRM model with/without an inhibitor. According to two Taylor flow model result, the BCM was able to analyze the internal flow in the simplified SRM combustion chamber. The BCM is proved to be valid for nozzle model because the result of CDV nozzle was qualitatively agreed with theoretical solution. According to the result of the simple SRM model, the BCM was able to predict flowfield in the SRM combustion chamber, even with the existence of an inhibitor. Throughout the computations, BCM solver was able to reproduce flows in the SRM combustion chamber, thus it is expected the approach has a great potential to apply for the internal flows in the complicated SRM combustion chamber.

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Section: Vecla Modelmentioning

confidence: 99%

Section: Methods 21 Taylor Flow Modelmentioning

confidence: 99%

Section: Vecla Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Two-dimensional computational fluid dynamics analysis of internal flow in a simplified solid rocket motor combustion chamber

Ogawa

Sasaki

2017

JFST

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“…이때 분출에 의하여 발생하는 축방향 유동 (injection-driven flow)은 하류방향의 분출 유동과 상호작용하면서 특정한 주파수 특성을 갖 는 유동으로 발전해 간다. 이와 같은 유동의 주 파수 특성은, 분출유동이 축-방향 유동과 상호작 용에 의하여 생성된 전단층 내에서 발생하는 와 흘림 (vortex shedding) 과 연관된 것으로 알려 져 있다 [10,11].…”

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Frequency Response of Turbulent Flow to Momentum Forcing in a Channel with Wall Blowing

Na¹,

Lee²

2010

Journal of the Korean Society for Aeronautical & Space Scie

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Due to the interaction between main oxidizer flow and the wall injected flow resulting from the regression process, a specific time characteristics identified in the frequency spectrum of streamwise velocity is generated in the hybrid rocket motor. In order to understand the response of the turbulent flow to two different types of external momentum forcing, LES analysis was conducted without considering the combustion. It turns out that both concentrated and distributed forcings do not lead to the disastrous resonance phenomenon. Energy contents are enhanced due to the added momentum but the peak frequency was not modified in the turbulent flow near the end of the rocket motor. Natural frequency of the flow system should be taken into account to further pursue the instability issue by using external forcing.

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Moderate‐to‐large injection and suction driven channel flows with expanding or contracting walls

2003

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We consider in this paper the incompressible laminar flow in a porous channel with expanding or contracting walls. While the head-end is closed by a compliant membrane, the downstream end is left unobstructed. For symmetric injection or suction along the uniformly expanding porous walls, the Navier-Stokes equations are reduced to a single, nonlinear, ordinary differential equation. The latter is obtained via similarity transformations in both time and space. The resulting equation is then solved both numerically and asymptotically, using perturbations in the crossflow Reynolds number R. Two separate approaches are presented for each of the injection and suction cases, respectively. For the large injection case, the governing equation is first integrated and the resulting third-order differential equation is solved using the method of variation of parameters. For the large suction case, the governing equation is first simplified near the wall and then solved using successive approximations. Results are then correlated and compared for variations in R and the dimensionless wall expansion rate α. For injection-induced flow, the asymptotic solution becomes more accurate when R/α is increased. Its deviation from the classic sinusoidal profile arising in nonexpanding channels becomes less significant with successive increases in R. For suction-induced flows, faster wall contractions increase the effective Reynolds number −(α + R), thus leading to more precise approximations. For the same absolute value of R, the suction-flow approximation tends to be the most accurate of the two and the least sensitive to variations in α. As −(α + R) is increased, the suction profile approaches the linear form anticipated in nonexpanding channels. By comparison with the injection-induced flow, suction is characterized by improved accuracy, sharper flow turning, and larger

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Flow instabilities and acoustic resonance of channels with wall injection

Cited by 63 publications

References 6 publications

Two-dimensional computational fluid dynamics analysis of internal flow in a simplified solid rocket motor combustion chamber

Two-dimensional computational fluid dynamics analysis of internal flow in a simplified solid rocket motor combustion chamber

Frequency Response of Turbulent Flow to Momentum Forcing in a Channel with Wall Blowing

Moderate‐to‐large injection and suction driven channel flows with expanding or contracting walls

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