Chapter 10 Introduction to Compressible Flow
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Che 253M Experiment No. 2 COMPRESSIBLE GAS FLOW
Rev. 8/15 AD/GW ChE 253M Experiment No. 2 COMPRESSIBLE GAS FLOW The objective of this experiment is to familiarize the student with methods for measurement of compressible gas flow and to study gas flow under subsonic and supersonic flow conditions. The experiment is divided into three distinct parts: (1) Calibration and determination of the critical pressure ratio for a critical flow nozzle under supersonic flow conditions (2) Calculation of the discharge coefficient and Reynolds number for an orifice under subsonic (non- choked) flow conditions and (3) Determination of the orifice constants and mass discharge from a pressurized tank in a dynamic bleed down experiment under (choked) flow conditions. The experimental set up consists of a 100 psig air source branched into two manifolds: the first used for parts (1) and (2) and the second for part (3). The first manifold contains a critical flow nozzle, a NIST-calibrated in-line digital mass flow meter, and an orifice meter, all connected in series with copper piping. The second manifold contains a strain-gauge pressure transducer and a stainless steel tank, which can be pressurized and subsequently bled via a number of attached orifices. A number of NIST-calibrated digital hand held manometers are also used for measuring pressure in all 3 parts of this experiment. Assorted pressure regulators, manual valves, and pressure gauges are present on both manifolds and you are expected to familiarize yourself with the process flow, and know how to operate them to carry out the experiment. A process flow diagram plus handouts outlining the theory of operation of these devices are attached. -
Laws of Similarity in Fluid Mechanics 21
Laws of similarity in fluid mechanics B. Weigand1 & V. Simon2 1Institut für Thermodynamik der Luft- und Raumfahrt (ITLR), Universität Stuttgart, Germany. 2Isringhausen GmbH & Co KG, Lemgo, Germany. Abstract All processes, in nature as well as in technical systems, can be described by fundamental equations—the conservation equations. These equations can be derived using conservation princi- ples and have to be solved for the situation under consideration. This can be done without explicitly investigating the dimensions of the quantities involved. However, an important consideration in all equations used in fluid mechanics and thermodynamics is dimensional homogeneity. One can use the idea of dimensional consistency in order to group variables together into dimensionless parameters which are less numerous than the original variables. This method is known as dimen- sional analysis. This paper starts with a discussion on dimensions and about the pi theorem of Buckingham. This theorem relates the number of quantities with dimensions to the number of dimensionless groups needed to describe a situation. After establishing this basic relationship between quantities with dimensions and dimensionless groups, the conservation equations for processes in fluid mechanics (Cauchy and Navier–Stokes equations, continuity equation, energy equation) are explained. By non-dimensionalizing these equations, certain dimensionless groups appear (e.g. Reynolds number, Froude number, Grashof number, Weber number, Prandtl number). The physical significance and importance of these groups are explained and the simplifications of the underlying equations for large or small dimensionless parameters are described. Finally, some examples for selected processes in nature and engineering are given to illustrate the method. 1 Introduction If we compare a small leaf with a large one, or a child with its parents, we have the feeling that a ‘similarity’ of some sort exists. -
Aerodynamics Material - Taylor & Francis
CopyrightAerodynamics material - Taylor & Francis ______________________________________________________________________ 257 Aerodynamics Symbol List Symbol Definition Units a speed of sound ⁄ a speed of sound at sea level ⁄ A area aspect ratio ‐‐‐‐‐‐‐‐ b wing span c chord length c Copyrightmean aerodynamic material chord- Taylor & Francis specific heat at constant pressure of air · root chord tip chord specific heat at constant volume of air · / quarter chord total drag coefficient ‐‐‐‐‐‐‐‐ , induced drag coefficient ‐‐‐‐‐‐‐‐ , parasite drag coefficient ‐‐‐‐‐‐‐‐ , wave drag coefficient ‐‐‐‐‐‐‐‐ local skin friction coefficient ‐‐‐‐‐‐‐‐ lift coefficient ‐‐‐‐‐‐‐‐ , compressible lift coefficient ‐‐‐‐‐‐‐‐ compressible moment ‐‐‐‐‐‐‐‐ , coefficient , pitching moment coefficient ‐‐‐‐‐‐‐‐ , rolling moment coefficient ‐‐‐‐‐‐‐‐ , yawing moment coefficient ‐‐‐‐‐‐‐‐ ______________________________________________________________________ 258 Aerodynamics Aerodynamics Symbol List (cont.) Symbol Definition Units pressure coefficient ‐‐‐‐‐‐‐‐ compressible pressure ‐‐‐‐‐‐‐‐ , coefficient , critical pressure coefficient ‐‐‐‐‐‐‐‐ , supersonic pressure coefficient ‐‐‐‐‐‐‐‐ D total drag induced drag Copyright material - Taylor & Francis parasite drag e span efficiency factor ‐‐‐‐‐‐‐‐ L lift pitching moment · rolling moment · yawing moment · M mach number ‐‐‐‐‐‐‐‐ critical mach number ‐‐‐‐‐‐‐‐ free stream mach number ‐‐‐‐‐‐‐‐ P static pressure ⁄ total pressure ⁄ free stream pressure ⁄ q dynamic pressure ⁄ R -
Stall/Surge Dynamics of a Multi-Stage Air Compressor in Response to a Load Transient of a Hybrid Solid Oxide Fuel Cell-Gas Turbine System
Journal of Power Sources 365 (2017) 408e418 Contents lists available at ScienceDirect Journal of Power Sources journal homepage: www.elsevier.com/locate/jpowsour Stall/surge dynamics of a multi-stage air compressor in response to a load transient of a hybrid solid oxide fuel cell-gas turbine system * Mohammad Ali Azizi, Jacob Brouwer Advanced Power and Energy Program, University of California, Irvine, USA highlights Dynamic operation of a hybrid solid oxide fuel cell gas turbine system was explored. Computational fluid dynamic simulations of a multi-stage compressor were accomplished. Stall/surge dynamics in response to a pressure perturbation were evaluated. The multi-stage radial compressor was found robust to the pressure dynamics studied. Air flow was maintained positive without entering into severe deep surge conditions. article info abstract Article history: A better understanding of turbulent unsteady flows in gas turbine systems is necessary to design and Received 14 August 2017 control compressors for hybrid fuel cell-gas turbine systems. Compressor stall/surge analysis for a 4 MW Accepted 4 September 2017 hybrid solid oxide fuel cell-gas turbine system for locomotive applications is performed based upon a 1.7 MW multi-stage air compressor. Control strategies are applied to prevent operation of the hybrid SOFC-GT beyond the stall/surge lines of the compressor. Computational fluid dynamics tools are used to Keywords: simulate the flow distribution and instabilities near the stall/surge line. The results show that a 1.7 MW Solid oxide fuel cell system compressor like that of a Kawasaki gas turbine is an appropriate choice among the industrial Hybrid fuel cell gas turbine Dynamic simulation compressors to be used in a 4 MW locomotive SOFC-GT with topping cycle design. -
A Semi-Hydrostatic Theory of Gravity-Dominated Compressible Flow
Generated using version 3.2 of the official AMS LATEX template 1 A semi-hydrostatic theory of gravity-dominated compressible flow 2 Thomas Dubos ∗ IPSL-Laboratoire de Météorologie Dynamique, Ecole Polytechnique, Palaiseau, France Fabrice voitus CNRM-Groupe d’étude de l’Atmosphere Metéorologique, Météo-France, Toulouse, France ∗Corresponding author address: Thomas Dubos, LMD, École Polytechnique, 91128 Palaiseau, France. E-mail: [email protected] 1 3 Abstract 4 From Hamilton’s least action principle, compressible equations of motion with density diag- 5 nosed from potential temperature through hydrostatic balance are derived. Slaving density 6 to potential temperature suppresses the degrees of freedom supporting the propagation of 7 acoustic waves and results in a sound-proof system. The linear normal modes and dispersion 8 relationship for an isothermal state of rest on f- and β- planes are accurate from hydrostatic 9 to non-hydrostatic scales, except for deep internal gravity waves. Especially the Lamb wave 10 and long Rossby waves are not distorted, unlike with anelastic or pseudo-incompressible 11 systems. 12 Compared to similar equations derived by Arakawa and Konor (2009), the semi-hydrostatic 13 system derived here possesses an additional term in the horizontal momentum budget. This 14 term is an apparent force resulting from the vertical coordinate not being the actual height 15 of an air parcel, but its hydrostatic height, i.e. the hypothetical height it would have after 16 the atmospheric column it belongs to has reached hydrostatic balance through adiabatic 17 vertical displacements of air parcels. The Lagrange multiplier λ introduced in Hamilton’s 18 principle to slave density to potential temperature is identified as the non-hydrostatic ver- 19 tical displacement, i.e. -
CFD Based Design for Ejector Cooling System Using HFOS (1234Ze(E) and 1234Yf)
energies Article CFD Based Design for Ejector Cooling System Using HFOS (1234ze(E) and 1234yf) Anas F A Elbarghthi 1,*, Saleh Mohamed 2, Van Vu Nguyen 1 and Vaclav Dvorak 1 1 Department of Applied Mechanics, Faculty of Mechanical Engineering, Technical University of Liberec, Studentská 1402/2, 46117 Liberec, Czech Republic; [email protected] (V.V.N.); [email protected] (V.D.) 2 Department of Mechanical and Materials Engineering, Masdar Institute, Khalifa University of Science and Technology, Abu Dhabi, UAE; [email protected] * Correspondence: [email protected] Received: 18 February 2020; Accepted: 14 March 2020; Published: 18 March 2020 Abstract: The field of computational fluid dynamics has been rekindled by recent researchers to unleash this powerful tool to predict the ejector design, as well as to analyse and improve its performance. In this paper, CFD simulation was conducted to model a 2-D axisymmetric supersonic ejector using NIST real gas model integrated in ANSYS Fluent to probe the physical insight and consistent with accurate solutions. HFOs (1234ze(E) and 1234yf) were used as working fluids for their promising alternatives, low global warming potential (GWP), and adhering to EU Council regulations. The impact of different operating conditions, performance maps, and the Pareto frontier performance approach were investigated. The expansion ratio of both refrigerants has been accomplished in linear relationship using their critical compression ratio within 0.30% accuracy. The results show that ± R1234yf achieved reasonably better overall performance than R1234ze(E). Generally, by increasing the primary flow inlet saturation temperature and pressure, the entrainment ratio will be lower, and this allows for a higher critical operating back pressure. -
MSME with Depth in Fluid Mechanics
MSME with depth in Fluid Mechanics The primary areas of fluid mechanics research at Michigan State University's Mechanical Engineering program are in developing computational methods for the prediction of complex flows, in devising experimental methods of measurement, and in applying them to improve understanding of fluid-flow phenomena. Theoretical fluid dynamics courses provide a foundation for this research as well as for related studies in areas such as combustion, heat transfer, thermal power engineering, materials processing, bioengineering and in aspects of manufacturing engineering. MS Track for Fluid Mechanics The MSME degree program for fluid mechanics is based around two graduate-level foundation courses offered through the Department of Mechanical Engineering (ME). These courses are ME 830 Fluid Mechanics I Fall ME 840 Computational Fluid Mechanics and Heat Transfer Spring The ME 830 course is the basic graduate level course in the continuum theory of fluid mechanics that all students should take. In the ME 840 course, the theoretical understanding gained in ME 830 is supplemented with material on numerical methods, discretization of equations, and stability constraints appropriate for developing and using computational methods of solution to fluid mechanics and convective heat transfer problems. Students augment these courses with additional courses in fluid mechanics and satisfy breadth requirements by selecting courses in the areas of Thermal Sciences, Mechanical and Dynamical Systems, and Solid and Structural Mechanics. Graduate Course and Research Topics (Profs. Benard, Brereton, Jaberi, Koochesfahani, Naguib) ExperimentalResearch Many fluid flow phenomena are too complicated to be understood fully or predicted accurately by either theory or computational methods. Sometimes the boundary conditions of real-world problems cannot be analyzed accurately. -
Chapter 5 Dimensional Analysis and Similarity
Chapter 5 Dimensional Analysis and Similarity Motivation. In this chapter we discuss the planning, presentation, and interpretation of experimental data. We shall try to convince you that such data are best presented in dimensionless form. Experiments which might result in tables of output, or even mul- tiple volumes of tables, might be reduced to a single set of curves—or even a single curve—when suitably nondimensionalized. The technique for doing this is dimensional analysis. Chapter 3 presented gross control-volume balances of mass, momentum, and en- ergy which led to estimates of global parameters: mass flow, force, torque, total heat transfer. Chapter 4 presented infinitesimal balances which led to the basic partial dif- ferential equations of fluid flow and some particular solutions. These two chapters cov- ered analytical techniques, which are limited to fairly simple geometries and well- defined boundary conditions. Probably one-third of fluid-flow problems can be attacked in this analytical or theoretical manner. The other two-thirds of all fluid problems are too complex, both geometrically and physically, to be solved analytically. They must be tested by experiment. Their behav- ior is reported as experimental data. Such data are much more useful if they are ex- pressed in compact, economic form. Graphs are especially useful, since tabulated data cannot be absorbed, nor can the trends and rates of change be observed, by most en- gineering eyes. These are the motivations for dimensional analysis. The technique is traditional in fluid mechanics and is useful in all engineering and physical sciences, with notable uses also seen in the biological and social sciences. -
Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles ------Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles
UOT Mechanical Department / Aeronautical Branch Gas Dynamics Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles -------------------------------------------------------------------------------------------------------------------------------------------- Chapter Sixteen / Plug, Underexpanded and Overexpanded Supersonic Nozzles 16.1 Exit Flow for Underexpanded and Overexpanded Supersonic Nozzles The variation in flow patterns inside the nozzle obtained by changing the back pressure, with a constant reservoir pressure, was discussed early. It was shown that, over a certain range of back pressures, the flow was unable to adjust to the prescribed back pressure inside the nozzle, but rather adjusted externally in the form of compression waves or expansion waves. We can now discuss in detail the wave pattern occurring at the exit of an underexpanded or overexpanded nozzle. Consider first, flow at the exit plane of an underexpanded, two-dimensional nozzle (see Figure 16.1). Since the expansion inside the nozzle was insufficient to reach the back pressure, expansion fans form at the nozzle exit plane. As is shown in Figure (16.1), flow at the exit plane is assumed to be uniform and parallel, with . For this case, from symmetry, there can be no flow across the centerline of the jet. Thus the boundary conditions along the centerline are the same as those at a plane wall in nonviscous flow, and the normal velocity component must be equal to zero. The pressure is reduced to the prescribed value of back pressure in region 2 by the expansion fans. However, the flow in region 2 is turned away from the exhaust-jet centerline. To maintain the zero normal-velocity components along the centerline, the flow must be turned back toward the horizontal. -
COMSOL Computational Fluid Dynamics for Microreactors Used in Volatile Organic Compounds Catalytic Elimination
COMSOL Computational Fluid Dynamics for Microreactors Used in Volatile Organic Compounds Catalytic Elimination Maria Olea 1, S. Odiba1, S. Hodgson1, A. Adgar1 1School of Science and Engineering, Teesside University, Middlesbrough, United Kingdom Abstract Volatile organic compounds (VOCs) are organic chemicals that will evaporate easily into the air at room temperature and contribute majorly to the formation of photochemical ozone. They are emitted as gases from certain solids and liquids in to the atmosphere and affect indoor and outdoor air quality. They includes acetone, benzene, ethylene glycol, formaldehyde, methylene chloride, perchloroethylene, toluene, xylene, 1,3-butadiene, butane, pentane, propane, ethanol, etc. Source of VOCs emission include paints, industrial processes, transportation activities, household products such as cleaning agents, aerosols, fuel and cosmetics. Catalytic oxidation is one of the most promising elimination techniques for VOCs as a result of it flexibility and energy saving. The catalytic materials enhance the chemical reactions that convert VOCs (through oxidation) into carbon dioxide and water. Removal of volatile organic compounds at room temperature has always been a challenge to researchers. Developing a catalyst which could completely oxidize the VOCs at very low temperature in order to avoid catalyst deactivation and promote energy saving has been the key focus among researchers in the recent years. Moreover, as the oxidation reaction is highly exothermic, the use of catalytic microreactors instead of packed bed reactors was considered. Microreactors are microfabricated catalytic chemical reactors with at least one linear dimension in the micrometer range. Usually, they consist of narrow channels and exhibit large surface area-to- volume ratios which leads to high heat and mass transfer properties. -
Normal and Oblique Shocks, Prandtl Meyer Expansion
Aerothermodynamics of high speed flows AERO 0033{1 Lecture 3: Normal and oblique shocks, Prandtl Meyer expansion Thierry Magin, Greg Dimitriadis, and Adrien Crovato [email protected] Aeronautics and Aerospace Department von Karman Institute for Fluid Dynamics Aerospace and Mechanical Engineering Department Faculty of Applied Sciences, University of Li`ege Wednesday 9am { 12:15pm February { May 2021 1 / 36 Outline Normal shock Total and critical quantities Oblique shock Prandtl-Meyer expansion Shock reflection and shock interaction 2 / 36 Outline Normal shock Total and critical quantities Oblique shock Prandtl-Meyer expansion Shock reflection and shock interaction 2 / 36 Normal shock relations (inviscid flow) Rankine-Hugoniot relations for steady normal shock σ = 0; v = u ex ; n = ex ! σn(U2 − U1) = (F · n)2 − (F · n)1 ρ2u2 = ρ1u1 2 2 ρ2u2 + p2 = ρ1u1 + p1 ρ2u2H2 = ρ1u1H1 I Eqs. also valid for non calorically perfect gases I Contact discontinuity when u2 = u1 = 0 ! p2 = p1 I Otherwise, the total enthalpy conservation can be expressed as 2 2 2 u cp p γ p2 u2 γ p1 u1 H2 = H1 with H = h+ ; h = ! + = + 2 R ρ γ − 1 ρ2 2 γ − 1 ρ1 2 I Non-linear algebraic system of 3 eqs. in 3 unknowns ρ2, u2, and p2 with closed solution expressed in function of dimensionless parameters: Machp number M1 = u1=a1 and specific heat ratio γ, with a1 = γRT1 3 / 36 Normal shock relations for calorically perfect gases For M1 > 1 (derivation given further in this section) 2 ρ2 u1 (γ+1)M1 I ρ = u = 2 > 1 1 2 2+(γ−1)M1 p2 = 1 + 2γ (M2 − 1) > 1 I p1 γ+1 1 γ−1 2 2 1+ 2 -
Introduction
CHAPTER 1 Introduction "For some years I have been afflicted with the belief that flight is possible to man." Wilbur Wright, May 13, 1900 1.1 ATMOSPHERIC FLIGHT MECHANICS Atmospheric flight mechanics is a broad heading that encompasses three major disciplines; namely, performance, flight dynamics, and aeroelasticity. In the past each of these subjects was treated independently of the others. However, because of the structural flexibility of modern airplanes, the interplay among the disciplines no longer can be ignored. For example, if the flight loads cause significant structural deformation of the aircraft, one can expect changes in the airplane's aerodynamic and stability characteristics that will influence its performance and dynamic behavior. Airplane performance deals with the determination of performance character- istics such as range, endurance, rate of climb, and takeoff and landing distance as well as flight path optimization. To evaluate these performance characteristics, one normally treats the airplane as a point mass acted on by gravity, lift, drag, and thrust. The accuracy of the performance calculations depends on how accurately the lift, drag, and thrust can be determined. Flight dynamics is concerned with the motion of an airplane due to internally or externally generated disturbances. We particularly are interested in the vehicle's stability and control capabilities. To describe adequately the rigid-body motion of an airplane one needs to consider the complete equations of motion with six degrees of freedom. Again, this will require accurate estimates of the aerodynamic forces and moments acting on the airplane. The final subject included under the heading of atmospheric flight mechanics is aeroelasticity.