Compressible ideal-gas turbulence subjected to homogeneous shear is investigated at the rapid distortion limit. Specific issues addressed are (i) the interaction between kinetic and internal energies and role of pressure-dilatation; (ii) the modifications to pressure-strain correlation and Reynolds stress anisotropy and (iii) the effect of the composition of velocity fluctuations (solenoidal vs. dilatational). Turbulence evolution is found to be strongly influenced by gradient Mach number, the initial solenoidal-to-dilatational ratio of the velocity field and the initial intensity of the thermodynamic fluctuations. The balance between the initial fluctuations in velocity and thermodynamic variables is also found to be very important. Any imbalance in the two fluctuating fields leads to high levels of pressure-dilatation and intense exchange. For a given initial condition, it is found that the interaction via the pressuredilatation term between the momentum and energy equations reaches a peak at an intermediate gradient Mach number. The energy exchange between internal and kinetic modes is negligible at very high or very low Mach number values due to lack of pressure dilatation. When present, the exchange exhibits oscillations even as the sum of the two energies evolves smoothly. The interaction between shear and solenoidal initial velocity field generates dilatational fluctuations; for some intermediate levels of shear Mach number dilatational fluctuations account for 20% of the total fluctuations. Similarly, the interaction between shear and initial dilatation produces solenoidal oscillations. Somewhat surprisingly, the generation of solenoidal fluctuations increases with gradient Mach number. Larger levels of pressure-strain correlation are seen with dilatational rather than solenoidal initial conditions. Anisotropies of solenoidal and dilatational components are investigated individually. The most interesting observation is that solenoidal and dilatational turbulence tend toward a one componential state but the energetic component is different in each case. As in incompressible shear flows, with solenoidal fluctuations, the streamwise (1,1) component of Reynolds stress is dominant. With dilatational fluctuations, the stream-normal (2,2) component is the strongest. Overall, the study yields valuable insight into the linear processes in high Mach number shear flows and identifies important closure modeling issues.

Large-eddy simulation is rapidly becoming the preferred method for calculations involving turbulent phenomena. However, filtering equations as performed in traditional LES procedures leads to significant problems. In this work we present some key components in the construction of a novel LES solver for compressible turbulent flow, designed to overcome most of the problems faced by traditional LES procedures. We describe the construction of the large-scale algorithm, which employs fairly standard numerical techniques to solve the Navier{Stokes equations. We validate the algorithm for both transonic and supersonic ow scenarios. We further explicitly show that the solver is capable of capturing boundary layer effects. We present a detailed derivation of the chaotic map termed the \compressible poor man's Navier{Stokes (CPMNS) equation" starting from the Navier{Stokes equations themselves via a Galerkin procedure, which we propose to use as the fluctuating component in the SGS model. We provide computational results to show that the chaotic map can produce a wide range of temporal behaviors when the bifurcation parameters are varied over their ranges of stable behaviors. Investigations of the overall dynamics of the CPMNS equation demonstrates that its use increases the potential realism of the corresponding SGS model.

abstract: Production from a high pressure gas well at a high production-rate encounters the risk of operating near the choking condition for a compressible flow in porous media. The unbounded gas pressure gradient near the point of choking, which is located near the wellbore, generates an effective tensile stress on the porous rock frame. This tensile stress almost always exceeds the tensile strength of the rock and it causes a tensile failure of the rock, leading to wellbore instability. In a porous rock, not all pores are choked at the same flow rate, and when just one pore is choked, the flow through the entire porous medium should be considered choked as the gas pressure gradient at the point of choking becomes singular. This thesis investigates the choking condition for compressible gas flow in a single microscopic pore. Quasi-one-dimensional analysis and axisymmetric numerical simulations of compressible gas flow in a pore scale varicose tube with a number of bumps are carried out, and the local Mach number and pressure along the tube are computed for the flow near choking condition. The effects of tube length, inlet-to-outlet pressure ratio, the number of bumps and the amplitude of the bumps on the choking condition are obtained. These critical values provide guidance for avoiding the choking condition in practice. / Dissertation/Thesis / M.S. Mechanical Engineering 2013

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[pt] Este trabalho propõe um método numérico de solução de escoamentos de fluidos compressíveis e incompressíveis a qualquer número de Mach em geometrias irregulares. Um sistema bidimensional de coordenadas curvilíneas não-ortogonais,coincidentes com os contornos físicos é utilizado. Os componentes cartesianos de velocidade são usados nas equações da quantidade de movimento e os covariantes na equação da continuidade. Seleciona-se a técnica de volumes finitos para discretizar as equações de conservação relacionadas aos princípios físicos, em regime permanente devido esta preservar a propriedade conservativa das equações e a sua con sistência física no processo numérico. Adota-se a configuração de malha co-localizada, avaliando-se todas as variáveis dependentes nos pontos centrais dos volumes são avaliados com esquemas Power-Law e Quick. Especial atenção é dada ao tratamento numérico das condições de contorno. O problema do acoplamento massa específica-pressão-velocidade é solucionado usando-se uma combinação das equações da continuidade, de quantidade de movimento linear e de uma equação de estado, gerando duas equações de correção da pressão. A primeira corrige a massa específica e a pressão, a segunda, o fluxo de massa e a velocidade. Propõe-se uma modificação da equação da correção da velocidade usando um termo de compensação do erro obtido na sua avaliação a fim de acelerar a convergência. Utilizam-se vários tipos de interpolação da massa específica na face, para minimizar as atenuações das variáveis, causadas pela falsa difusão. Para a solução das equações algébricas resultantes usa-se o algoritmo TDMA linha por linha e um processo de correção por blocos para acelerar a convergência. O método proposto é verificado em seis problemas testes, através da comparação com os resultados analíticos e numéricos disponíveis na literatura. / [en] The present work consists in the development of a numerical method of solution of compressible and incompressible fluid flow for all speed in iregular geometries. A boundary-fitted two-dimensional nonorthogonal curvilinear coordinate systeam is utilized. The cartesian velocity components are the dependent variables in the momentum equations and covariant velocity components are used in the continuity equation. The finite-volume technique was selected to discretuze the steady-state physical phenomenon conservation equations, since this method keeps the conservative property of the equations and its physical consistency in the numerical process. A nonstaggered grid was employed, and all dependent variables are evaluated at the cell center points, which divides the physical domain. The convection-diffusion fluxes at the control volumes faces are evaluated with the Power Law and Quick shemes. Special attention is paid to the numerical treatment of boundary conditions. The problem of velocity-pressure-density coupling is solved using a combination of continuity, momentum equations and state equation resulting in two pressure correction equations. The first equation corrects the density and the pressure, the second equation corrects the mass flux and the velocity. A modification in the velocity correction equations is proposed using a compensationterm to accelerate the convergence. Several types of interpolation of the face density are used to reduce variable atenuations, caused by false diffusion. For the solution of the resulting algebric equations,the line-by-line TDMA algorith is used as well as a block-correction method to accelerate the convergence. The proposed method is verified on six test problems,by comparing the present results with analytical and numerical results avaiable in the literature.

No description available.

The difficulties regarding the control of high velocity flying vehicles in supersonic/hypersonic flight regime are still prevailing. Whether it is mixing enhancement,side force generation or aerodynamic steering, wall cooling or any otherfavourable method to control the flow, the resultant effects of different flow controltechniques on the associated flowfield demands careful experimental and numericalinvestigations. Traditional aerodynamic control surfaces are subjected tosevere flight conditions and loadings in different flight regimes resulting in impairedthe control effectiveness. Active flow control methods serve strong alternativeto achieve separation postponement, transition control, lift enhancement,mixing enhancement, drag reduction, turbulence modification and/or noise suppression,etc. This thesis deals with two main active flow control techniques;transverse jets at Mach 5 cross flow and energy deposition using arc discharge atMach 5 flow. The influence of roughness on the control effectiveness of transversejet interactions is also examined. The first objective of this thesis is to investigate experimentally the flowphysics of the sonic transverse jets at Mach 5 laminar cross flow both in timeaveraged and time resolved manner to provide reliable experimental data andbetter understanding at high Mach numbers. The parameters such as momentumflux ratio, incoming Reynolds number, type of the gas and the surface roughnessare studied. The size and structures of the upstream and downstream separationregions and jet penetration characteristics together with jet shear layer behaviourare examined. Moreover CFD simulations are conducted on a two dimensionalcase of Spaid and Zukoski and the numerical solver/procedure is validated. Thena three dimensional experimental case is simulated to provide greater understandingon the flow physics as well as to cross check measurements. As the main finding; jet interaction flow field can not be oversimplified andrepresented with only one parameter that is momentum flux ratio, J, as suggested by the literature; the incoming Reynolds number, type of injectant and roughnessare clearly affecting the interaction resulting in advantages or drawbacks for flowcontrol point of view. The second objective of this thesis is to investigate experimentally the dynamicsbetween the localised energy spot and the blunt body shock for dragreduction at Mach 5 flow. The localised energy spot is created firstly via steadyelectric arc struck between two electrodes using a small amount of energy andsecondly via pulsed laser focusing with a significant amount of energy. In caseof electric discharge, the effects of discharge are evaluated in comparison to nodischarge case with the electrodes. The unsteady wake/compression structuresare examined between the steadily deposited energy spot and the modified bowshock wave. And for the laser focussing unsteady interaction that is happeningin a short duration of time is investigated. The effect of the truncation, the distancebetween the electrodes and the model as well as the type and amount ofthe energy input on this phenomenon are examined. Moreover CFD simulationsare conducted on the baseline cases to cross check measurements together withtheoretical estimates. As the main finding; the effectiveness of the arc discharge is increasing withincreased truncation or the frontal area and when the arc to nose distance isthe shortest. However an important thing to note is that energy deposition atshorter distances might result higher stagnation point heating rates which aredetrimental. The test campaign clearly renders that the use of small amount ofonboard energy to create a local focused thermal spot in front of a vehicle is anefficient way of reducing drag.

The use of origami-based bellows is of interest in fields where traditional metal bellows are incapable of meeting compression, mass, or flexibility constraints. Metal bellows are often used in space applications but frequently complicate spacecraft design. Origami-based bellows capable of meeting design constraints while adequately shielding sensitive spacecraft parts may be advantageous to space mechanism design. The design and testing of a highly compressible origami bellows for harsh environments is described. Several origami patterns were evaluated and the Kresling fold pattern was designed to meet constraints and selected for use in the bellows design. Origami bellows were prototyped in five different materials and tested in fatigue, thermal cycling, ablation, and radiation. Tested bellows show good fatigue life exceeding 100,000 cycles for some materials and resilience to potential harsh environmental conditions such as thermal cycling, abrasion, and high radiation. The bellows can be designed to fit within a given inner and outer diameter and stroke length depending on the design requirements. The origami bellows shows promise for space application and as an adequate replacement for current metal bellows due to its high compressibility and low mass. The design, testing, and fabrication of an origami-based bellows for microgravity drilling is presented. The benefits of origami created an opportunity for application on NASA's Asteroid Redirect Mission (ARM) to protect sensitive parts from debris. Origami-based bellows were designed to fit spacial limitations and meet needed compression ratios. Designs have demonstrated high mass reductions, improved stroke length, greatly decreased stowed volume, improved flexibility, and reduced reaction forces in comparison with traditional metal bellows. Material and design testing demonstrated that a nylon-reinforced polyvinyl fluoride based bellows with an aramid fiber stitched seam is well suited for debris containment in space conditions. Various epoxies were able to maintain an adequate bond with polyvinyl fluoride below expected environmental temperature for bellows mounting to the ARM drill. Asymmetric compression of the bellows can occur at extreme low temperatures and is preventable by balancing stiffness within the structure.

Cette thèse traite par simulation numérique les écoulements turbulents compressibles avec transferts de chaleur, en relation avec les applications moteurs-fusées. Elle concerne, plus particulièrement, les systèmes de refroidissement des chambres de combustion. Le fluide refroidissant circule dans un état supercritique (haute pression et basse température) dans des canaux millimétriques, entourant la chambre de combustion. Ces problèmes font appel à une physique assez complexe et mettent en jeu un couplage fort entre les aspects compressibles et les transferts thermiques, en plus des phénomènes liés à la thermodynamique supercritique. D’un point de vue numérique, deux solveurs spécifiques ont été utilisés dans le cadre de cette thèse. Il s’agit, d’une part, du code CHOC-WAVES développé au CORIA pour la partie compressible et onde de choc et, d’autre part, le code PPMBFS développé à l’Université de Pennsylvanie (USA) pour les applications supercritiques et avec une thermodynamique variable. Sur le plan de la modélisation physique, l’approche LES a été utilisée, en appui des simulations DNS. Dans ce contexte, un modèle de sous-maille thermique, pour la prise en compte du Prandtl turbulent variable, a été intégré et validé. Les résultats obtenus, dans le cadre des LES et DNS d’un canal supersonique refroidi, ont permis de mieux analyser les corrélations aérothermiques ainsi que les structures cohérentes présentes au sein de cet écoulement. En particulier, il a été montré les limites de l’hypothèse de l’Analogie Forte de Reynolds (SRA) dans le cas d’écoulements fortement anisothermes, et le rôle joué par les structures tourbillonnaires dans l’accentuation des transferts pariétaux. La problématique des gaz réels a été ensuite examinée dans le cadre d’un canal industriel (en l’occurence EH3C). Cette étude a permis de mettre en évidence les difficultés (à la fois numérique et physique) liées à ce type d’écoulement. Les différentes investigations ont permis de fournir des informations utiles, notamment en ce qui concerne la phénoménologie des structures cohérentes et les différentes corrélations aérothermodynamiques. / This research deals with the numerical simulation of compressible turbulent flows with heat transfers, applied to rocket engines. It relates more particularly the cooling of combustion chambers, in which a fluid flows in a supercritical state (high pressure and low temperature) inside millimeter channels. These problems involve complex physical phenomena and coupling between compressible aspects and heat transfer phenomena as well as supercritical thermodynamics. From a numerical point of view, two specific solvers have been used in the context of this thesis. The first code (CHOC-WAVES) has been developed in the CORIA lab for compressible flows and shock waves. The second one (PPMBFS) has been developed at the Pennsylvania University for applications with supercritical thermodynamics variables. In terms of physical modeling, the LES approach has been widely used in support of DNS. In this context, a thermal subgrid model using a variable turbulent Prandtl number has been integrated and validated. A supersonic cooled channel has been simulate dusing both LES and DNS techniques and its results have been carefully analysed through the aerothermics correlations and coherent structures. In particular, it has been shown that the Strong Reynolds Analogy hypothesis (SRA), in the case of a strongly anisothermal flow is not valid anymore. The wall heat flux had an impact on the coherent structures. The issue of real gases was then examined through the industrial channel flow simulation (EH3C). This study has high lighted the difficulties (both numerical and physical) associated with this type of flow. The various investigations have provided useful information, especially regarding the phenomenology of coherent structures and various aerothermodynamics correlations.

<p> Continuous development of Gas Turbines to realise higher work output has necessitated the design of turbine blades having large turning angles.</p> <p> Improvements to existing calculation methods have been carried out to better describe the potential flow near the leading and trailing edges of a blade originally designed by R. K. Malhotra at McMaster University. An incompressible turbulent boundary layer program has been extended to calculate compressible flows, taking into account the adverse and favourable pressure gradients, and it has been used to describe the flow in the region near to the blade surface. </p> <p> A test facility of the intermittent blow-down type was constructed and instrumented to test two-dimensional blade cascades. Some of the blades were instrumented to measure the surface pressure distribution. The performance of the blades has been analysed both theoretically and experimentally over a range of angles of attack and pressure ratios. The effect of stagger angle was also investigated to show its effect on performance. The experimental results were compared to those obtained theoretically, and the agreement substantiates the main thrust of the thesis, which was to develop a rational design technique.</p> / Thesis / Doctor of Philosophy (PhD)