DOCSLIB.ORG

Performance Evaluation of an IC Engine in the Presence of a C-D Nozzle in the Air Intake Manifold

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Performance Evaluation of an IC Engine in the Presence of a C-D Nozzle in the Air Intake Manifold International Journal of Current Engineering and Technology ISSN 2277 - 4106 © 2013 INPRESSCO. All Rights Reserved. Available at http://inpressco.com/category/ijcet Research Article Performance Evaluation of an IC Engine in the Presence of a C-D Nozzle in the Air Intake Manifold S.Ravi Babu*a, K.Prasada Raoa and P.Ramesh Babua aDepartment of Mechanical Engineering, GMR Institute of Technology, Rajam, India Accepted 10 August 2013, Available online 01 October 2013, Vol.3, No.4 (October 2013) Abstract The present day energy crisis and ever increasing demands of energy in addition to global pollution brought us into a situation where there is an urgent need for energy conservation, efficient utilization and eco-friendly techniques to be implemented in day to day use. These needs lead us to an idea of modified design in a CI engine without any additional energy requirement and with no complicated variations in design. There are various other methods to improve the efficiency of engine such as super charging, turbo charging, varying stroke length, varying injection pressure, fuel to air ratio, additional strokes per cycle and so on. Many of them require additional design (stroke length, injection pressure etc.,) and some of them load to increase environmental effect. Here in this project affords were made to increase the velocity (physical parameter) of air entering the inlet manifold of the engine by inserting a convergent divergent nozzle at the inlet manifold. There by increasing the mixture quality of air & fuel in the combustion chamber before the initialization of ignition. The engine load tests were carried out at different loads, variation of different parameters with load was plotted. The nozzle setup was installed and then again load test were carried out at different loads and the values were plotted in comparison to former values. The emissions from the engine were also tested before and after the setup installation to estimate the environmental effects. The comparative results were also plotted. Keywords: I.C Engine, diesel engine, Performance characteristics, Emission control. 1. Introduction piezoelectric wafers in lieu of a solenoid, giving finer control of the injection event (M.chandramouli et al, 1A diesel engine (also known as a compression-ignition 2009). Variable geometry turbochargers have flexible engine) is an internal combustion engine that uses the heat vanes, which move and let more air into the engine of compression to initiate ignition to burn the fuel that has depending on load. This technology increases both been injected into the combustion chamber. The diesel performance and fuel economy. Boost lag is reduced as engine has the highest thermal efficiency of any regular turbo impeller inertia is compensated for. Accelerometer internal or external combustion engine due to its very high pilot control (APC) uses an accelerometer to provide compression ratio. Low-speed diesel engines (as used in feedback on the engine's level of noise and vibration and ships and other applications where overall engine weight thus instruct the ECU to inject the minimum amount of is relatively unimportant) can have a thermal efficiency fuel that will produce quiet combustion and still provide that exceeds 50%. Diesel engines are manufactured in the required power (especially while idling). The next two-stroke and four-stroke versions. They were originally generation of common rail diesels is expected to use used as a more efficient replacement for stationary steam variable injection geometry, which allows the amount of engines. Since the 1910s they have been used in fuel injected to be varied over a wider range (Mohan raj et submarines and ships. Use in locomotives, trucks, heavy al, 2009), and variable valve timing (see Mitsubishi's equipment and electric generating plants followed later. In 4N13 diesel engine) similar to that on petrol engines. the 1930s, they slowly began to be used in a few Particularly in the United States, coming tougher automobiles. Since the 1970s, the use of diesel engines in emissions regulations present a considerable challenge to larger on road and off-road vehicles in the USA increased. diesel engine manufacturers. Ford's HyTrans Project has As of 2007, about 50% of all new car sales in Europe are developed a system which starts the ignition in 400 ms, diesel. saving a significant amount of fuel on city routes, and As of 2013, many common rail and unit injection there are other methods to achieve even more efficient systems already employ new injectors using stacked combustion, such as homogeneous charge compression ignition, being studied. Japanese and Swedish vehicle manufacturers are also developing diesel engines that run *Corresponding author: S.Ravi Babu 1158 S.Ravi Babu et al International Journal of Current Engineering and Technology, Vol.3, No.4 (October 2013) on dimethyl ether (DME) (Asad et al, 2009). Some recent is nearly constant). At subsonic flow the gas is diesel engine models utilize a copper alloy heat exchanger compressible; sound, a small pressure wave, will technology to take advantage of benefits in terms of propagate through it. At the throat, where the cross thermal performance, heat transfer efficiency, sectional area is a minimum, the gas velocity locally strength/durability, corrosion resistance, and reduced becomes sonic (Mach number = 1.0), a condition called emissions from higher operating temperatures. choked flow. As the nozzle cross sectional area increases M.Chandramouli et al. (M.chandramouli et al, 2009) the gas begins to expand and the gas flow increases to selected a four stroke compression ignition engine with supersonic velocities where a sound wave will not power 9 H.P and rated speed 1500 rpm to investigate the propagate backwards through the gas as viewed in the performance characteristics. The swirl motion of the air is frame of reference of the nozzle (Mach number > 1.0). an important parameter in optimizing the performance of A de Laval nozzle will only choke at the throat if the the engine. In order to increase the air velocity in the inlet pressure and mass flow through the nozzle is sufficient to manifold a convergent-divergent nozzle is used. The rise reach sonic speeds, otherwise no supersonic flow is in velocity with the use of nozzle generates turbulence at achieved and it will act as a venturi tube; this requires the the exit of the manifold which facilitates for better entry pressure to the nozzle to be significantly above combustion of injected fuel. The Performance ambient at all times (equivalently, the stagnation pressure characteristics were calculated with nozzle and without of the jet must be above ambient). nozzle in the inlet manifold and compared (V.CVS Phaneendra et al, 2009). 2. Analysis of gas flow in De Laval nozzles. A de Laval nozzle (or convergent-divergent nozzle, CD nozzle) is a tube that is pinched in the middle, making The analysis of gas flow through de Laval nozzles a carefully balanced, asymmetric hourglass-shape. It is involves a number of concepts and assumptions: used to accelerate a hot, pressurized gas passing through it For simplicity, the gas is assumed to be an ideal gas. to a supersonic speed, and upon expansion, to shape the The gas flow is isentropic (i.e., at constant entropy). exhaust flow so that the heat energy propelling the flow is As a result the flow is reversible (frictionless and no maximally converted into directed kinetic energy. Because dissipative losses), and adiabatic (i.e., there is no heat of this, the nozzle is widely used in some types of steam gained or lost). turbines, and is used as a rocket engine nozzle. It also sees The gas flow is constant (i.e., steady) during the use in supersonic jet engines (Ganeshan). period of the propellant burn. The gas flow is along a straight line from gas inlet to exhaust gas exit (i.e., along the nozzle's axis of symmetry) The gas flow behavior is compressible since the flow is at very high velocities (Mach number > 0.3). 2.1 Exhaust gas velocity As the gas enters a nozzle, it is traveling at subsonic velocities. As the throat contracts down the gas is forced to accelerate until at the nozzle throat, where the cross sectional area is the smallest, the linear velocity becomes sonic. From the throat the cross sectional area then increases, the gas expands and the linear velocity becomes progressively more supersonic. The linear velocity of the exiting exhaust gases can be calculated using the following equation 1 TR 2 P [1 ] M 1 p Where Fig.1 De-laval nozzle showing approximate velocity (v), = Exhaust velocity at nozzle exit m/s together with the effect on temperature (T) and pressure T= absolute temperature of inlet gas, K (P). R= Universal gas law constant=8314.5 j/(kmol-k) M= the gas molecular mass, kg/kmol Its operation relies on the different properties of gases = isentropic expansion factor flowing at subsonic and supersonic speeds. The speed of a C = specific heat of the gas at constant pressure subsonic flow of gas will increase if the pipe carrying it p C = specific heat of the gas at constant volume narrows because the mass flow rate is constant. The gas v P= absolute pressure of exhaust gas at nozzle exit, Pa flow through a de Laval nozzle is isentropic (gas entropy 1159 S.Ravi Babu et al International Journal of Current Engineering and Technology, Vol.3, No.4 (October 2013) 3. Design of the nozzle the fuel is injected directly into the cylinder. The increased turbulence causes better cooling of the cylinder surfaces thereby reducing the heat loss to the surroundings. The heat from the cylinder walls gets absorbed by the air supplied during suction and used for reducing the delay period thereby increasing the thermal efficiency of the engine.
Load more

Recommended publications
  • Rocket Nozzles: 75 Years of Research and Development
    Sådhanå Ó (2021) 46:76 Indian Academy of Sciences https://doi.org/10.1007/s12046-021-01584-6Sadhana(0123456789().,-volV)FT3](0123456789().,-volV) Rocket nozzles: 75 years of research and development SHIVANG KHARE1 and UJJWAL K SAHA2,* 1 Department of Energy and Process Engineering, Norwegian University of Science and Technology, 7491 Trondheim, Norway 2 Department of Mechanical Engineering, Indian Institute of Technology Guwahati, Guwahati 781039, India e-mail: [email protected]; [email protected] MS received 28 August 2020; revised 20 December 2020; accepted 28 January 2021 Abstract. The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design. The principal parameters in this context are the shape of the nozzle contour and the nozzle area expansion ratio. A careful shaping of the nozzle contour can lead to a high gain in its performance. As a consequence of intensive research, the design and the shape of rocket nozzles have undergone a series of development over the last several decades. The notable among them are conical, bell, plug, expansion-deflection and dual bell nozzles, besides the recently developed multi nozzle grid. However, to the best of authors’ knowledge, no article has reviewed the entire group of nozzles in a systematic and comprehensive manner. This paper aims to review and bring all such development in one single frame. The article mainly focuses on the aerodynamic aspects of all the rocket nozzles developed till date and summarizes the major findings covering their design, development, utilization, benefits and limitations.
    [Show full text]
  • Session 15 FLOWS THROUGH NOZZLE Outline
    Session 15 FLOWS THROUGH NOZZLE Outline • Definition • Types of nozzle • Flow analysis • Ideal Gas Relationship • Mach Number and Speed of Sound • Isentropic flow of an ideal gas • De Laval nozzle • Nozzle efficiency • Calculation examples Definition Nozzle is a duct by flowing through which the velocity of a fluid increases at the expense of pressure drop. A duct which decreases the velocity of a fluid and causes a corresponding increase in pressure is called a diffuser Types of Nozzles There are three types of nozzles a. Convergent nozzle b. Divergent nozzle c. Convergent-divergent nozzle Flow Analysis • Incompressible flow • Compressible Flow The variation of fluid density for compressible flows requires attention to density and other fluid property relationships. The fluid equation of state, often unimportant for incompressible flows, is vital in the analysis of compressible flows. Also, temperature variations for compressible flows are usually significant and thus the energy equation is important. Curious phenomena can occur with compressible flows. Flow Analysis • For simplicity, the gas is assumed to be an ideal gas. • The gas flow is isentropic. • The gas flow is constant • The gas flow is along a straight line from gas inlet to exhaust gas exit • The gas flow behavior is compressible Ideal Gas Relationship The equation of state for an ideal gas is: For an ideal gas, internal energy, û is considered to be a function of temperature only Thus, Ideal Gas Relationship The fluid property enthalpy, ĥ is defined as Since for an ideal gas, enthalpy is a function of temperature only, the ideal gas specific heat at constant pressure, Cp can be expressed as And, Ideal Gas Relationship We see that changes in internal energy and enthalpy are related to changes in temperature by values of Cp and Cv.
    [Show full text]
  • Cdf Study of Biphasic Fluid in Convergent-Divergent De
    CDF STUDY OF BIPHASIC FLUID IN CONVERGENT-DIVERGENT DE LAVAL NOZZLE Maricruz Hernández-Hernández1, Victor Hugo Mercado-Lemus1, Hugo Arcos Gutiérrez2, Isaías Garduño-Olvera2, Adriana Del Carmen Gallegos Melgar1, Jan Mayen2, Raul Pérez Bustamante1. 1CONACYT, Corporación Mexicana de Investigación en Materiales, Saltillo, Coahuila, C.P. 25290, México. 2CONACYT, CIATEQ, Unidad San Luis Potosí, Eje 126 No. 225, Zona Industrial, San Luis Potosí C.P. 78395, México. Abstract Results The fluid behavior in a convergent-divergent nozzle employed in Cold spray process is numerically analyzed. Cold spray, also called Cold gas dynamic spray, has a high potential, both for the generation of coatings and for the additive manufacturing technique. One of the main components of this equipment is the spray gun, its configuration is highly important in the control of the final characteristics of the coating, and in the efficiency of the process. Gas dynamics are responsible for delivering a power at a desired velocity and temperature. A high-pressure gas flows into a de Laval Figure 1:Geometry domain and boundary conditions of nozzle. nozzle with the ability to accelerate compressible fluids at supersonic speeds, largely determined by the nozzle configuration. The transporter gas operates in an adiabatic, reversible regimen, and calorically perfect - mean the gas behavior is governed by isentropic flow relation. In this work, the gas dynamic behavior in two different nozzle geometry is numerically analyzed using OpenFOAM under compressible conditions. Introduction In the Laval nozzle, dissipative effects like viscosity and heat transfer occur mainly in thin boundary layers near the nozzle walls. This means that a large part of the gas operates in an adiabatic, reversible regimen.
    [Show full text]
  • Supersonic Air and Wet Steam Jet Using Simplified De Laval Nozzle
    Proceedings of the International Conference on Power Engineering-15 (ICOPE-15) November 30- December 4, 2015, Yokohama, Japan Paper ID: ICOPE-15-1158 Supersonic air and wet steam jet using simplified de Laval nozzle Takumi Komori*, Masahiro Miura*, Sachiyo Horiki* and Masahiro OSAKABE* * Tokyo University of Marine Science & Technology 2-1-6Etchujima, Koto-ku, Tokyo 135-8533, Japan E-mail: [email protected] Abstract Usually, Trichloroethane has been used for the de-oiling and cleaning of machine parts. But its production and import have been prohibited since 1995 because of its possibility to destroy the ozone layer. Generally for biological and environmental safety, the de-oiling should be done with the physical method instead of the chemical method using detergent or solvent. As one of the physical method, a cleaning by a supersonic wet steam jet has been proposed. The steam jet with water droplets impinges on the oily surface of machine parts and removes the oil or smudge. In the present study, the low-cost and taper-shaped nozzles were fabricated with an electric discharge machining. The jet behaviors from the taper-shaped nozzles were carefully observed by using air and wet steam. The non-equilibrium model of wet steam was proposed and compared with the experimental results. The spatial distribution of low density regions along the jet axis was considered to contribute the cleaning and de-oiling. However, the condensate generated with the depressurization of steam depressed the injected steam mass flow rate. Furthermore, the steam cleaning was conducted for the plastic coin and the good cleaning effect could be confirmed in spite of the short cleaning duration.
    [Show full text]
  • Flow Analysis of Rocket Nozzle Using Method of Characteristics
    FLOW ANALYSIS OF ROCKET NOZZLE USING METHOD OF CHARACTERISTICS Dipen R. Dangi1, Parth B. Thaker2, Atal B. Harichandan3 1, 2, 3 Department of Mechanical Engineering, Marwadi Education Foundation, (India) ABSTRACT The present research work has been carried out for the analysis of bell type nozzle by using method of characteristic with different Mach number conditions. A C-code has been developed to define the nozzle geometry by using method of characteristics usually designed for De-Laval nozzle. ANSYS 14.0 has been used for the present flow analysis by considering hear Stress Transport k-ω (SSTKW) turbulence model. In this paper CFD is used to develop best geometry of rocket nozzle with consider of aero - thermodynamic property like pressure, velocity, temperature and Mach number. Keywords: Design Of Supersonic Nozzle, Method Of Characteristic And Minimum Length Of Nozzle. I INTRODUCTION Performance of rocket nozzle is always less than the theoretical approach in all practical approaches. It is always essential to improve the performance of rocket nozzle. Previous research works show the De- Laval nozzle is the most efficient nozzle among all other types of nozzles. The De-Laval nozzle gives the best performance rocket nozzle as Mach number and velocity of fluid flow is continuously increasing while at same time pressure is continuously decreasing. But still some research gap is there to develop best geometry of rocket nozzle. Even today most of the engineers are work on how to develop best geometry of rocket nozzle and to achieve higher Mach number and higher velocity of fluid flow. Due to that reason authors works on the Method of Characteristics (MOC) and developed best geometry which gives possible optimum values of Mach number, velocity, pressure distribution and density distribution.
    [Show full text]
  • Rocket Nozzles the Simplest Nozzle Is a Cone with a Half-Opening Angle, Α Attached to a Combustion Chamber (See Figure 3)
    NOZZLES S. R. KULKARNI 1. Motivation In astronomy textbooks it is usually stated that the Bondi-Hoyle solution has a specific value for the accretion rate (given the boundary conditions of ambient density and temper- ature of the gas). Only with this specific accretion rate will there be a seamless transition from sub-sonic inflow to super-sonic inflow. The Bondi-Hoyle or the Parker problem is quite analogous to the rocket problem, in that both involve a smooth transition from sub-sonic to super-sonic flow. What bothered me is the statement in astronomy books that the solution demands a specific accretion (or excretion) mass rate. In contrast, the thrust on a rocket can be varied (as can be gathered if you watch NASA TV). Given the similarity between the astronomical problem and the rocket problem I thought an investigation of the latter may be illuminating and hence this note. 2. The de Laval Nozzle Consider a rocket which is burning fuel. Let M˙ be the burn rate of the fuel and ue be the speed of the exhaust. Then in steady state the vertical “thrust” or force is Mu˙ e. The resulting vertical thrust lifts the rocket. Clearly, it is of greatest advantage to make the exhaust speed as large as possible and to minimize the outflow in directions other than vertical. A rocket engine consists of a chamber in which fuel is burnt connected to a nozzle. A properly designed1 nozzle can convert the hot burnt fuel into supersonic flow (see Figure 1). The integration of the momentum equation (under assumptions of inviscid flow) yields the much celebrated Beronulli’s theorem.
    [Show full text]
  • Characterization of Non-Equilibrium Condensation of Supercritical Carbon Dioxide in a De Laval Nozzle
    Characterization of Non-Equilibrium Condensation of Supercritical Carbon Dioxide in a de Laval Nozzle The MIT Faculty has made this article openly available. Please share how this access benefits you. Your story matters. Citation Lettieri, Claudio, Derek Paxson, Zoltan Spakovszky, and Peter Bryanston-Cross. “Characterization of Non-Equilibrium Condensation of Supercritical Carbon Dioxide in a de Laval Nozzle.” Volume 9: Oil and Gas Applications; Supercritical CO2 Power Cycles; Wind Energy (June 26, 2017). As Published http://dx.doi.org/10.1115/GT2017-64641 Publisher ASME International Version Final published version Citable link http://hdl.handle.net/1721.1/116087 Terms of Use Article is made available in accordance with the publisher's policy and may be subject to US copyright law. Please refer to the publisher's site for terms of use. Proceedings of ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition GT2017 June 26-30, 2017, Charlotte, NC, USA GT2017-64641 CHARACTERIZATION OF NON-EQUILIBRIUM CONDENSATION OF SUPERCRITICAL CARBON DIOXIDE IN A DE LAVAL NOZZLE Claudio Lettieri Derek Paxson Delft University of Technology Massachusetts Institute of Technology Delft, The Netherlands Cambridge, MA, USA Zoltan Spakovszky Peter Bryanston-Cross Massachusetts Institute of Technology Warwick University Cambridge, MA, USA Coventry, UK ABSTRACT data, with improved accuracy at conditions away from the On a ten-year timescale, Carbon Capture and Storage could critical point. The results are applied in a pre-production significantly reduce carbon dioxide (CO2) emissions. One of supercritical carbon dioxide compressor and are used to define the major limitations of this technology is the energy penalty inlet conditions at reduced temperature but free of for the compression of CO2 to supercritical conditions, which condensation.
    [Show full text]
  • Design of a Small-Scaled De Laval Nozzle for IGLIS Experiment
    Design of a small-scaled de Laval nozzle for IGLIS experiment Evgeny Mogilevskiy, R. Ferrer, L. Gaffney, C. Granados, M. Huyse, Yu. Kudryavtsev, S. Raeder, P. Van Duppen Instituut voor Kern- en Stralingsfysika, KU Leuven, Celestijnenlaan 200 D, B-3001 Leuven, Belgium. Outline • IGLIS technique and requirements for a gas jet • Classical way of a nozzle design – Method of characteristics – Boundary layer correction • Iterative method based on CFD with COMSOL • Conclusions and further steps IGLIS= In Gas Laser Ionization Spectroscopy Differential Gas cell chamber Extraction pumping chamber chamber S-shaped RFQ de Laval nozzle Gas Cell Ion collector Towards mass Gas jet separator gas Extraction RFQ Extraction electrode from in-flight separator One-dimension laser beam expander Thing Position of the λ1 λ2 λ2 λ1 entrance stopped nuclei In-gas-jet window In-gas-cell ionization ionization 1·10-5-2·10 -3 -2 < 1e-5 mbar 1·10 -2 mbar mbar •Products of a nuclear reaction get into the gas cell (Argon or Helium, 500 mbar) •Atoms are neutralized and stopped in the cell, then transported towards the nozzle •Two-step ionization is used for resonance ionization of the specified element Requirements for the jet • Cold enough with no pressure (high Mach number) – No Doppler and pressure broadening • Long enough with no shocks (uniform) – Enough space and time to light up all the atoms • Small enough flow rate – Pumping system capacity Small scaled de Laval nozzle is required De Laval Nozzle Convergent-divergent nozzle: A – area of a cross-section, V – gas velocity, M – Mach number Pressure, temperature and density along the nozzle Quantitative characteristics Parameter Aeronautics [1] Chemical study [2] IGLIS[3] Stagnation pressure 10^3 atm 10^(-5) atm 10^(-1) atm Stagnation 2000K 300K 300 K temperature Throat size 3 mm 25 mm 1 mm Exit Mach number 6 to 15 4 8 to 12 Gas Air Helium Argon Reynolds number 10^6 4000 3000 (in throat) [1] J.J.
    [Show full text]
  • Space Advantage Provided by De-Laval Nozzle and Bell Nozzle Over Venturi
    Proceedings of the World Congress on Engineering 2015 Vol II WCE 2015, July 1 - 3, 2015, London, U.K. Space Advantage Provided by De-Laval Nozzle and Bell Nozzle over Venturi Omkar N. Deshpande, Nitin L. Narappanawar Abstract:-The FSAE guidelines state that it is mandatory for many crucial components are to be fitted in a very little each and every car participating in the said event to have a space. Therefore there is a need to design a new kind of single circular 20mm restrictor in the intake system. All the air nozzle achieving optimality at a higher angle than that of the flowing to the engine must pass through this restrictor. Conventionally, a Venturi Nozzle is used as a restrictor. In our venturi nozzle. For this purpose De Laval Nozzle and Bell research, we have proposed two Nozzles: De-Laval Nozzle and Nozzle are analyzed as a possible alternative to the venturi. Bell Nozzle as an alternative to the Venturi Nozzle. After De- Laval Nozzle is used in certain type of steam turbines numerous CFD Simulations; we have inferred that the results and also as a Rocket Engine Nozzle [6]. Bell Nozzle is also of the De-Laval Nozzle and Bell Nozzle are similar to the widely used as a Rocket Engine Nozzle. Both of the nozzles Venturi Nozzle. Along with providing similar results, the two achieve optimality at a higher angle of convergence as nozzles provide a space saving of 6.86% over the Venturi Nozzle. The data was gathered from SolidWorks Flow demonstrated in ‘Section V parts A.); B.).’ Simulation 2014.
    [Show full text]
  • Section1: " Compressible Flow: Historical Perspective and Basic Definitions!
    Section1: " Compressible Flow: Historical Perspective and Basic Definitions! Anderson: Chapter 1 pp. 1-19! 1! MAE 5420 - Compressible Fluid Flow! De Laval Nozzle! • High Speed flows often seem “counter-intuitive” when! Compared with low speed flows! • Example: Convergent-Divergent Nozzle (De Laval)! !In 1897 Swedish Engineer Gustav De Laval designed! !!A turbine wheel powered by 4- steam nozzles! !!De Laval Discovered that if the steam nozzle ! Credit: NASA!! GSFC! first narrowed, and then expanded, the efficiency of! !!the turbine was increased dramatically ! flow !!Furthermore, the ratio of the minimum area! !!to the inlet and outlet areas was critical for achieving! !!maximum efficiency … Counter to the “wisdom” of the day! Convergent / Divergent Nozzle 2! MAE 5420 - Compressible Fluid Flow! De Laval Nozzle (cont’d)! • Mechanical Engineers of the 19’th century were! Primarily “hydrodynamicists” .. That is they were! Familiar with fluids that were incompressible … liquids! and Low speed gas flows where fluid density was! Essentially constant! • Primary Principles are Continuity and Bernoulli’s Law! 3! MAE 5420 - Compressible Fluid Flow! De Laval Nozzle (cont’d)! • When Continuity and Bernoulli are applied to a ! De Laval Nozzle and density is Assumed constant! High Pressure Inlet! pI! pe! pt! VI! A A Ve! I At Vt! e AI! A ! Ae! ! t ! At Throat! ! • Pressure Drop! • Velocity Increases! Continuity! Bernoulli! “classic” Venturi! 4! MAE 5420 - Compressible Fluid Flow! De Laval Nozzle (cont’d)! • When Continuity and Bernoulli are applied to a ! De
    [Show full text]
  • Concepts and Cfd Analysis of De-Laval Nozzle
    International Journal of Mechanical Engineering and Technology (IJMET) Volume 7, Issue 5, September–October 2016, pp.221–240, Article ID: IJMET_07_05_024 Available online at http://iaeme.com/Home/issue/IJMET?Volume=7&Issue=5 Journal Impact Factor (2016): 9.2286 (Calculated by GISI) www.jifactor.com ISSN Print: 0976-6340 and ISSN Online: 0976-6359 © IAEME Publication CONCEPTS AND CFD ANALYSIS OF DE-LAVAL NOZZLE Malay S Patel, Sulochan D Mane and Manikant Raman Mechanical Engineering Department, Dr. D.Y Patil Institute of Engineering and Technology, Pune, India. ABSTRACT Anozzle is a device designed to control the characteristics of fluid. It is mostly used to increase the velocity of fluid. A typical De-Laval nozzle is a nozzle which has a converging part, throat and diverging part. This paper aims at explaining most of the concepts related to De Laval nozzle. In this paper the principle of working of nozzle is discussed. Theoretical analysis of flow is also done at different points of nozzle. The variation of flow parameters like Pressure, Temperature, Velocity and Density is visualized using Computational Fluid Dynamics. The simulation of shockwave through CFD is also done. Key words: Rocket engine nozzle, De-Laval nozzle, Ideal gas, Computational Fluid dynamics, Ansys-Fluent. Cite this Article: Malay S Patel, Sulochan D Mane and Manikant Raman, Concepts and CFD Analysis of De-Laval Nozzle. International Journal of Mechanical Engineering and Technology, 7(5), 2016, pp. 221–240. http://iaeme.com/Home/issue/IJMET?Volume=7&Issue=5 1. INTRODUCTION
    [Show full text]
  • Preliminary Design Document ASEN 4018
    Preliminary Design Document ASEN 4018 1 of 28 American Institute of Aeronautics and Astronautics Preliminary Design Document ASEN 4018 Contents 2 Project Description 3 2.1 Project Purpose . 3 2.2 Objectives . 3 2.3 CONOPS . 4 2.4 Functional Block Diagram . 5 2.5 Functional Requirements . 6 3 Design Requirements 7 4 Key Design Options Considered 9 4.1 Nozzle Design . 9 4.1.1 de Laval Nozzle . 10 4.1.2 Annular Convergent-Divergent Nozzle (ACD Nozzle) . 10 4.1.3 Variable Geometry Nozzle . 11 4.1.4 Expansion-Deflection Nozzle . 12 4.1.5 Minimum Length Nozzle (MLN) . 13 4.1.6 Heat Transfer for Flow Velocity Control . 13 4.2 Nozzle Testbed . 14 4.2.1 Testing on JetCat Engine vs. Engine Analogue . 14 4.2.2 Hot-flow vs. Cold-flow Testbed . 15 4.2.3 Actual Size vs. Scaled Nozzle . 17 4.3 Nozzle Integration . 18 4.3.1 Complete Nozzle Replacement . 18 4.3.2 Nozzle extension and Overlapping Extension . 19 4.3.3 Nozzle Dome Replacement . 21 5 Trade Study Process and Results 23 5.1 Nozzle Design . 23 5.1.1 Trade Elements . 23 5.1.2 Trade Study . 23 5.2 Nozzle Testbed . 24 5.2.1 Trade Elements . 24 5.2.2 Trade Study . 25 5.3 Nozzle Integration . 25 5.3.1 Trade Elements . 25 5.3.2 Trade Study . 26 6 Selection of Baseline Design 26 6.1 Nozzle Aerodynamics . 26 6.2 Nozzle Test Bed . 27 6.3 Nozzle Integration . 27 2 of 28 American Institute of Aeronautics and Astronautics Preliminary Design Document ASEN 4018 2.
    [Show full text]