Vorticity generation and acoustic resonance of simulated solid rocket motor chamber with high wave number wall injection

Hegab, A.

doi:10.1016/j.compfluid.2008.12.001

Cited by 5 publications

(14 citation statements)

References 29 publications

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“…Using the expended variables used in Hegab [7] and inserting them in (1), the side wall steady vorticity generation (Ω | wall ) and the accompanying heat transfer ( / | wall ) are derived and written as follows:…”

Section: The Physical and Mathematical Formulationmentioning

confidence: 99%

“…The second one is the unsteady flow computation based on initial conditions as computed from the first step. The perturbation theory introduced by Staab et al [11] and applied by Hegab [7] leads to the following weakly rotational equations:…”

Section: The Physical and Mathematical Formulationmentioning

confidence: 99%

“…Here, the NSCBC technique applied by [7] is presented in detail. The full derivation for the parabolized Navier-Stokes at the upper and lower boundaries and at the head and exit ends is formulated to specify the nonphysical conditions at these boundaries.…”

Section: The Computational Approachmentioning

confidence: 99%

“…The experimental results are recorded for flow in a channel with fully transpired wall. Three different porous surfaces using three different sizes of honeycomb cells are used, [7]. In this figure, a comparison between the analytical and the numerical solutions at the midlength of the chamber is illustrated.…”

Section: Code Validationsmentioning

confidence: 99%

“…In order to have a stable rocket system with desirable performance, individual study for the combustion model that incorporates the burning of microscale propellant and the nonreactive model that accounts the complex fluid flow inside the chamber and the nozzles must be examined first. Some recent studies that consider the burning of microscale solid rocket propellant [1][2][3][4][5][6] concluded that the injection conditions of the cold models in [7][8][9][10][11][12][13][14] are found to be different than that considered with the reactive models [1][2][3][4][5][6]. As a result, the current study is conducted to examine the unsteady flow field inside the solid rocket motor chamber and the complex generated wave and vorticity patterns and their impact on the burning of real solid propellant surfaces.…”

Section: Introductionmentioning

confidence: 99%

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Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

Hegab

Sait

Hussain

2015

Mathematical Problems in Engineering

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An advanced and intensive computational solution development is integrated with an asymptotic technique, to examine the impact of the combustion surface morphology on the generated rotational flow field in a solid rocket chamber with wide ranges of forcing frequencies. The simulated rectangular chamber is closed at one end and is open at the aft end. The upper and lower walls are permeable to allow steady and unsteady injected air to generate internal flow mimicking the flow field of the combustion gases in real rocket chamber. The frequencies of the unsteady injected flow are chosen to be very close or away from the resonance frequencies of the adapted chamber. The current study accounts for a wide range of wave numbers that reflect the complexity of real burning processes. Detailed derivation for Navier-Stokes equations at the four boundaries of the chamber is introduced in the current study. Qualitative comparison is performed with recent experimental work carried out on a two-inch hybrid rocket motor using a mixture of polyethylene and aluminum powder. The higher the percentage of aluminum powder in the mixture, the more the corrugations of the combustion surface. This trend is almost similar to the computational and analytical results of a simulated solid rocket chamber.

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Section: The Physical and Mathematical Formulationmentioning

confidence: 99%

Section: The Physical and Mathematical Formulationmentioning

confidence: 99%

Section: The Computational Approachmentioning

confidence: 99%

Section: Code Validationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

Hegab

Sait

Hussain

2015

Mathematical Problems in Engineering

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Simulation of a nonstationary flow in a channel with a distributed blow from the channel walls and forced pressure oscillations

Волков

2013

J Eng Phys Thermophy

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A nonstationary flow in a channel with a blow was simulated on the basis of the Reynolds-averaged NavierStokes equations and the two-parameter k-ε model of turbulence. The pressure near the left end of the channel changes by the harmonic law. It was established that the k-ε model of turbulence can be used for calculating the nonstationary flows formed in the indicated channel by a blow.Introduction. The oscillations of the parameters of a working substance in the combustion chamber of a solid-propellant engine (SPE) represent a dangerous effect that can disturb the normal working conditions of the engine and, in some cases, cause its failure. These oscillations are due to the vibrating combustion or the hydrodynamic instability of the flow of the fuel combustion products.A model of a fluid flow in a channel with permeable walls can be used for simulation of a flow of combustion products in the channel of an SPE charge because this model reflects the significant process of transfer of a solid fuel from the burning surface of the charge. However, in the indicated model, the decomposition and combustion of the fuel in the thin near-surface layer of the charge are not taken into account.The inner flow of a working substance in the channel of an SPE is turbulent, and complex physical processes proceed in the working space of the SPE against the background of its general gasdynamic state. The turbulence of the gas flow in the indicated channel influences its characteristics and intensifies the heat transfer at the surfaces of the prenozzle space and the nozzle unit of the SPE. The nonstationarity of this gas flow can be caused, e.g., by a change in the rate of gas blow along the generatrix of the channel or by the forced oscillations of the pressure near the left (closed) end of the channel.A laminar flow of an incompressible viscous fluid in a straight round tube with a nonstationary blow was investigated in [1,2]. The stationary solution of this problem obtained in [3] (the rate of blow along the generatrix of the cylinder was assumed to be constant) shows that the disturbances arising near the left closed end of the tube lead to the formation of a plane acoustic field in it. The interaction of this field with the fluid blown into the tube leads to the generation of a vortex along its side surface. Between the side surface of the tube and the line found at a distance of half the radius of the tube from its symmetry axis, there arise large radial gradients of the axial flow velocity [4].The nonstationary calculations carried out in [5] show that the vorticity of a flow of an incompressible viscous fluid in a tube is inversely proportional to the Mach number, which is in agreement with the theoretical data [3,6] and the numerical calculations [7]. The axial derivative of the radial flow velocity is of the order of O(M

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Effect of the head cavity on pressure oscillation suppression characteristics in large solid rocket motors

Zhang

Wang

et al. 2015

Sci. China Technol. Sci.

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Vorticity generation and acoustic resonance of simulated solid rocket motor chamber with high wave number wall injection

Cited by 5 publications

References 29 publications

Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

Simulation of a nonstationary flow in a channel with a distributed blow from the channel walls and forced pressure oscillations

Effect of the head cavity on pressure oscillation suppression characteristics in large solid rocket motors

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