Numerical simulation of cooling gas injection using adaptive multiresolution techniques

Dahmen, Wolfgang; Gotzen, Thomas; Melian, Sorana; Müller, Siegfried

doi:10.1016/j.compfluid.2012.10.003

Cited by 15 publications

(17 citation statements)

References 33 publications

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“…The numerical results have been compared to and are in very good agreement with experimental investigations; see, e.g., [13], (biglobal) linear stability theory; see, e.g., [33,34], and other numerical simulations; see, e.g., [6,34]. In the following, the extended binary gas-mixture NS3D simulation is compared to 1) an analytical solution of a simple self-diffusion problem, 2) previous air-in-air film-cooling results obtained by experiments and simulations, and 3) foreign-gas film-cooling experiments and other simulations.…”

Section: Code Verification and Validationsupporting

confidence: 63%

“…The first procedure is simply known as film cooling. Here, the coolant is injected through a single spanwise slit or row of holes, either by blowing in the (inclined) wall-normal direction (see, e.g., [2][3][4][5][6]) or by wall-parallel blowing through a backward-facing step (see, e.g., [7][8][9][10][11]). When blowing through multiple, uniformly distributed, discrete holes or slits, this is labeled effusion cooling; see, e.g., [12][13][14].…”

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confidence: 99%

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Influence of Cooling-Gas Properties on Film-Cooling Effectiveness in Supersonic Flow

Keller

Kloker

Olivier

2015

Journal of Spacecraft and Rockets

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Film cooling is considered a prerequisite for the safe operation of future high-performance rocket engines. Wallnormal or inclined cooling-gas injection into a laminar boundary-layer airflow at Mach 2.6 through a single infinite spanwise slit with various cooling gases using direct numerical simulations and experiments are investigated. Among the investigated gases, helium and hydrogen perform best with respect to cooling effectiveness and skin friction decrease. An arbitrary variation of various cooling-gas parameters shows that the diffusion coefficient has virtually no influence on the cooling effectiveness, whereas low cooling-gas viscosity, low thermal conductivity, high heat capacity, low molar mass, and low density are highly beneficial. In light of this large number of parameters, an extension of the single-species cooling-effectiveness correlation to binary gas-mixture flows is challenging, if possible at all. Nomenclature C = Chapman-Rubesin factor c = mass fraction c f = skin friction coefficient c p = heat capacity at constant pressure c v = heat capacity at constant volume D = ordinary diffusion coefficient D T = thermal diffusion coefficient e = internal energy F = blowing rate I = identity matrix j = diffusion mass-flux vector k = Boltzmann constant L = characteristic length M = molar mass Ma = Mach number Pr = Prandtl number p = pressure q = heat-flux vector R = gas constant Re u = unit Reynolds number Re ∞ = global Reynolds number Sc = Schmidt number T = temperature t = time v = velocity vector X = mole fraction x s = slit position x, y, z = streamwise, spanwise, and wall-normal directions α = blowing angle or thermal diffusion rate η = cooling effectiveness ϑ = thermal conductivity κ = specific heat ratio μ = dynamic viscosity ξ = correlation parameter ϵ = second Lennard-Jones parameter ρ = density σ = first Lennard-Jones parameter Ω = transport collision integral Subscripts c = cooling-gas values (species 2) i = species i is = isothermal uc = uncooled w = values at wall ∞ = freestream values (species 1) Superscripts = Eckert values ⋆ = dimensional values

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Section: Code Verification and Validationsupporting

confidence: 63%

mentioning

confidence: 99%

Influence of Cooling-Gas Properties on Film-Cooling Effectiveness in Supersonic Flow

Keller

Kloker

Olivier

2015

Journal of Spacecraft and Rockets

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“…Gotzen et al 7 demonstrated previously, that QUADFLOW is capable of simulating the injection of ideal gases in an efficient and accurate manner. 13 The accuracy of the current simulation of various gas mixtures shall be verified by comparison with experimental data.…”

Section: Va Quadflow Solvermentioning

confidence: 97%

“…For this purpose we employ the scientific research code QUADFLOW. The cooling gas injection of air into air modeled as an ideal gas has already been simulated by Gotzen et al 7 In the current study, we are going to analyze the influence of different coolants to provide deeper insight into the effect of the coolant on the flow field and the wall heat fluxes.…”

Section: Introductionmentioning

confidence: 98%

Numerical Simulation of Coolant Variation in Laminar Supersonic Film Cooling

Windisch

Reinartz

Mueller

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Film cooling is investigated numerically for slot injection on a flat plate. Here, the influence of different cooling gases on the resulting cooling layer is of particual interest. Air, helium, argon, carbon dioxide and sulfur(VI)fluoride are used as coolants. The numerical simulations are performed with the adaptive, parallel flow-solver QUADFLOW. The results are compared with recent experimental data. 1

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“…The computational grids are represented by block-structured parametric B-spline patches. All the key ingredients have been described in detail in the theses by Bramkamp [21], Lamby [22], and Müller [23], followed by numerous publications in which the solver has been extended and applied to a wide range of problems from subsonic to hypersonic flows, together with a thorough validation; for example, some recent publications are [24][25][26][27][28][29]. By now the QUADFLOW solver, as well as the underlying numerical methods, are well established.…”

Section: B Numerical Methodsmentioning

confidence: 98%

Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

2016

Self Cite

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Edney type IV and type VII shock-shock interactions are complex hypersonic flow phenomena. They are characterized by a supersonic jet that reaches far into the flowfield. An experimental investigation of the inner jet structure is difficult, especially in cases where the jet is subject to high-frequency unsteady movements. The present paper provides insight into the jet structure and its movement by means of a highly resolved computational fluid dynamics analysis in thermochemical nonequilibrium that significantly exceeds the resolution of existing publications. Simulations of an Edney type IV interaction in nitrogen flow are presented. Advanced adaptation strategies allow for the identification and analysis of the mechanisms of the jet unsteadiness, resulting in a new classification of the unsteady flowfield behavior with respect to the periodic jet movement. This classification is based not only on wall quantities, but also on the core flowfield. The computations are supplemented by a grid sensitivity study. The second configuration is an Edney type VII interaction. This shock-shock interaction type was observed and defined in nitrogen flow by Yamamoto et al (Numerical Investigation of Shock/Vortex Interaction in Hypersonic Thermochemical Nonequilibrium Flow, Journal of Spacecraft and Rockets, Vol. 36, No. 2, 1999, pp. 240-246. The present results demonstrate that this interaction may also be observed in carbon-dioxide-dominated flow with a gas composition similar to the Martian atmosphere. The results provide insight into the jet structure of this less known interaction.

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Numerical simulation of cooling gas injection using adaptive multiresolution techniques

Cited by 15 publications

References 33 publications

Influence of Cooling-Gas Properties on Film-Cooling Effectiveness in Supersonic Flow

Influence of Cooling-Gas Properties on Film-Cooling Effectiveness in Supersonic Flow

Numerical Simulation of Coolant Variation in Laminar Supersonic Film Cooling

Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

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