Utilizing Flow Simulation in the Design Phase of a Casting Die to Optimize Design Parameters and Defect Analysis

2017 ◽  
Vol 4 (8) ◽  
pp. 9256-9263 ◽  
Author(s):  
Priyanka Vispute ◽  
Digambar Chaudhari
Keyword(s):  
Flow Simulation ◽  
Design Parameters ◽  
Design Phase ◽  
Defect Analysis ◽  
Optimize Design

Design and Analysis of a Marine Current Turbine

2017 ◽  
Author(s):  
T. Karthikeyan ◽  
E. J. Avital ◽  
N. Venkatesan ◽  
A. Samad
Keyword(s):  
Pitch Angle ◽  
Flow Simulation ◽  
Ocean Current ◽  
Power Coefficient ◽  
Design Parameters ◽  
Marine Current Turbine ◽  
Commercial Code ◽  
Marine Current ◽  
Current Turbine ◽  
Blade Pitch Angle

Ocean stores a huge amount of energy and ocean current energy can be a viable source in future. In this article, an axial marine current turbine has been optimized to enhance its power coefficient through numerical modeling. The blade pitch-angle and number of blades are the design parameters chosen for the analysis to find the optimal design. A commercial code for CFD simulations with in-house optimization code was used for the analysis. It was found that, changing the blade pitch-angle and reducing the number of blades can improve the turbine’s coefficient of power. This is due to increase in lift and reduction of losses caused by turbulence near the downstream of the turbine. The article presents flow-simulation difficulties and characteristic curves to identify the differences between the actual and optimized turbine. The detailed flow physics is discussed and pictured in the post processed plots.

A computational model of the flight dynamics and aerodynamics of a jellyfish-like flying machine

2017 ◽  
Vol 819 ◽  
pp. 621-655 ◽  
Author(s):  
Fang Fang ◽  
Kenneth L. Ho ◽  
Leif Ristroph ◽  
Michael J. Shelley
Keyword(s):  
Aerodynamic Force ◽  
Fast Multipole Method ◽  
Flow Simulation ◽  
Ground Effect ◽  
Vortex Sheet ◽  
Mirror Image ◽  
Design Parameters ◽  
Efficiency Increase ◽  
Wake Model ◽  
Opening And Closing

We explore theoretically the aerodynamics of a recently fabricated jellyfish-like flying machine (Ristroph & Childress, J. R. Soc. Interface, vol. 11 (92), 2014, 20130992). This experimental device achieves flight and hovering by opening and closing opposing sets of wings. It displays orientational or postural flight stability without additional control surfaces or feedback control. Our model ‘machine’ consists of two mirror-symmetric massless flapping wings connected to a volumeless body with mass and moment of inertia. A vortex sheet shedding and wake model is used for the flow simulation. Use of the fast multipole method allows us to simulate for long times and resolve complex wakes. We use our model to explore the design parameters that maintain body hovering and ascent, and investigate the performance of steady ascent states. We find that ascent speed and efficiency increase as the wings are brought closer, due to a mirror-image ‘ground-effect’ between the wings. Steady ascent is approached exponentially in time, which suggests a linear relationship between the aerodynamic force and ascent speed. We investigate the orientational stability of hovering and ascent states by examining the flyer’s free response to perturbation from a transitory external torque. Our results show that bottom-heavy flyers (centre of mass below the geometric centre) are capable of recovering from large tilts, whereas the orientation of the top-heavy flyers diverges. These results are consistent with the experimental observations in Ristroph & Childress (J. R. Soc. Interface, vol. 11 (92), 2014, 20130992), and shed light upon future designs of flapping-wing micro aerial vehicles that use jet-based mechanisms.

Structural Deformation and Stress Analysis of Aircraft Wing by Finite Element Method

2014 ◽  
Vol 906 ◽  
pp. 318-322 ◽  
Author(s):  
M. Fazlay Rabbey ◽  
Anik Mahmood Rumi ◽  
Farhan Hasan Nuri ◽  
Hafez M. Monerujjaman ◽  
M. Mehedi Hassan
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Structural Properties ◽  
Structural Deformation ◽  
Design Parameters ◽  
Design Phase ◽  
Aircraft Wing ◽  
Detail Design ◽  
The Cost ◽  
Element Method

Wing of an aircraft is lift producing component. It makes aircraft airborne by generating lift>weight. The wing must take the full aircraft weight during flying. So, it is very sophisticated task for designing a wing by keeping consideration of every design parameters simultaneously. This paper contains analysis of structural properties of wing by using finite element method. For well-organized design all the variables must be considered from the beginning of the design phase. The design phases for aircraft are: conceptual, preliminary and detail design. Until the preliminary design phase the aircraft structure is not considered. During these phases the material of the wing should be selected in such a way so that it can perform efficiently with less unexpected phenomena (drag) for which responsible properties are displacement, stress etc. Currently the most focusing area for the aero-elastic investigation is to design wing with good aerodynamic shape which will associated with less dragging structural behavior. It helps to reduce SFC (Specific Fuel Consumption) and so the cost. The analysis on that has done through Computational means as well as simulation technique to develop knowledge about the variation of aircraft wing structural properties.

Engineering Design Analysis Tool for Early Design Phase With Low-Fidelity Models: A Case of Hydraulic Crane

2017 ◽  
Author(s):  
Asko Ellman ◽  
Sami Pajunen ◽  
Ilari Laine ◽  
Eric Coatanea
Keyword(s):  
Engineering Design ◽  
Design Analysis ◽  
Design Parameters ◽  
Analysis Tool ◽  
Design Phase ◽  
Early Design ◽  
Standard Design ◽  
Hydraulic Crane ◽  
Early Design Phase

Model-based product design using computer simulation has become a standard design practice in most companies in mechanical engineering. However, there is a need for efficient simulation tools that can provide design-supporting information already at early design phase when the most important decisions are made. Design process and design tools need to be agile and enable iterative process where the design and its requirements can effectively be iterated. Low-fidelity models can be part of the solution for time issue in early design phase. Low-fidelity prototypes are simplified representations of functions and concepts in the virtual prototype. Axiomatic design with low-fidelity modelling approach is a promising concept for achieving design-supporting information in an efficient way. In this method, there is a linear mapping between design parameters and system characteristics. Non-linear models of the system are linearized at the nominal point. An engineering design analysis tool (EDA tool) to enhance EDA is constructed and presented in this paper. For evaluation of the usefulness of this tool, a case study is presented. The case study deals with a simple hydraulic crane that is manufactured from steel plate. The results of the case study design are compared with results achieved with conventional CAD and FEM tools. Modelling accuracy and required modelling and simulation efforts are compared in both cases.

Numerical Flow Simulation in the Induction System of an Internal Combustion Engine

1992 ◽  
Author(s):  
S. Y. Ho ◽  
A. J. Przekwas
Keyword(s):  
Internal Combustion Engine ◽  
Stokes Equations ◽  
Combustion Engine ◽  
Flow Simulation ◽  
Internal Combustion ◽  
Flow Fields ◽  
The Body ◽  
Design Parameters ◽  
Complex Flow ◽  
Induction System

Abstract An advanced computational fluid dynamics package, REFLEQS, has been adapted to calculate the flow in the induction system of an internal combustion engine. Results of complex flow fields in multi-valve engine intake/exhaust ports and cylinders, including moving valves and piston, are calculated. The body-fitted structured grids generated with partial differential equations method have been applied to represent complex engine components configuration such as engine intake/exhaust ports, ducts, valves and cylinders. An upwind scheme combined with SIMPLEC method is employed to solve the Navier-Stokes equations. Several 2D and 3D flows in engine ports/cylinders are simulated. Complex flow fields involve separated flows near the entry of cylinder head, vortices near the corner and behind the valves and the valve/stem generated swirling and tumbling flows. The present work aims at establishing a generalized computational environment for analyzing the physical mechanisms and design parameters controlling internal flows in automotive air/fuel induction systems.

Side Impact Safety Design of Vehicle Based on Implicit Parametric Technology

2014 ◽  
Vol 635-637 ◽  
pp. 631-636
Author(s):  
Tao Chen ◽  
Yun Peng
Keyword(s):  
Safety Performance ◽  
Side Impact ◽  
Simplified Model ◽  
Design Parameters ◽  
Impact Model ◽  
Design Phase ◽  
Concept Design ◽  
Safety Design

In the concept design phase of new car development, the parametric simplified side impact model was established by implicit parametric technology. The design parameters of BIW were optimized based on simplified model, such as the shape of section and the thickness of parts. The side impact safety performance and lightweight requirements were set as restraints during optimizing. The case indicated that the intrusion and intrusive velocity of B-pillar were reduced more than 30% and the mass was reduced 5.6% by this method.

Design, Fabrication, and Realization of a Supersonic Wind Tunnel for Educational Purposes

2009 ◽  
Vol 37 (4) ◽  
pp. 286-303 ◽  
Author(s):  
Mohammed K. Ibrahim ◽  
A. F. Abohelwa ◽  
Galal B. Salem
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Compressible Flows ◽  
Basic Education ◽  
Design Parameters ◽  
High Tech ◽  
Design Phase ◽  
Supersonic Wind Tunnel ◽  
Design Error ◽  
Standard Textbook

The supersonic wind tunnel is an indispensable facility for basic education in any course that covers compressible flows and one of the main pillars of any aerodynamic laboratory. The introduction of a supersonic wind tunnel at the aerodynamics laboratory of the Aerospace Engineering Department at Cairo University had often been postponed and was hindered by a lack of funds for the purchase of foreign equipment and expertise. Thoughts therefore turned to building such facility instead of buying it, substituting high-tech and complex foreign equipment for locally produced equipment, and ‘thinking out of the box’ to make the most use of available resources, even when this led to some unconventional applications. An extensive scheme for the design, fabrication, and realization of a multi-Mach number ( M = 1.5, 2, and 2.5) supersonic wind tunnel for laboratory experiments is proposed in this paper. The proposed scheme is simple, detailed and multi-level; it starts by utilizing one-dimensional isentropic flow theory for the conceptual design phase and makes full use of computational fluid dynamics at the detailed design phase. This ensured that we had a working design before we embarked on the manufacture of any components, which would have been costly to modify had there been any design error. A parametric study has been carried out for a number of design parameters, using numerical simulations. After the design and fabrication, a number of successful standard textbook experiments, for Mach number 2, were carried out as validation for the proposed scheme. The results showed good agreement with the theoretical predictions.

Optimum Design of Remote Controller Back Shell Injection Mould Based on Flow Simulation

2014 ◽  
Vol 852 ◽  
pp. 567-572
Author(s):  
Jian Ming Hong
Keyword(s):  
Mass Production ◽  
Time Pressure ◽  
Influence Factors ◽  
Flow Simulation ◽  
Design Parameters ◽  
Process Technology ◽  
Flow Process ◽  
Mould Design ◽  
Trapped Gas ◽  
Remote Controller

Taking the remote controller back shell for example, the flow process of the injection molding including filling, packing, holding and cooling was simulated by using the process technology of Moldflow software, the best gate location and the information of weld lines, trapped gas, fill time, pressure and temperature were analyzed. At the same time, the product defects during the injection was predicted, the cause of defects and influence factors was analyzed, the mould design parameters were adjusted, the design of the mould was optimized. It realized mass production of the product.

scholarly journals Calculation of airgap function and inductance using analytical modeling of rotor magnetic characteristics of an IPM motor under loaded condition

2021 ◽  
Author(s):  
BINITA NANDA ◽  
Praveen Kumar
Keyword(s):  
Optimal Design ◽  
Energy Conversion ◽  
Analytical Model ◽  
Motor Performance ◽  
Analytical Modeling ◽  
Design Parameters ◽  
Magnetic Characteristics ◽  
Design Phase ◽  
Initial Design ◽  
The Relationship

<div>This paper proposes an analytical model to calculate the airgap function and inductance, which can be used to get an optimal design during the initial design phase. It investigates the relationship between the design parameters of the rotor and the motor performance.</div><div><br></div><div>This paper is under review in IEEE Transactions on Energy Conversion.<br></div>

scholarly journals Modelling of green water ingress into holds of an open-top containership in its preliminary design phase

2009 ◽  
Vol 16 (1) ◽  
pp. 3-7 ◽  
Author(s):  
Tomasz Cepowski
Keyword(s):  
Ship Design ◽  
Green Water ◽  
Occurrence Rate ◽  
Design Parameters ◽  
Preliminary Design ◽  
Design Phase ◽  
Conceptual Approach ◽  
Operational Conditions ◽  
Water Ingress ◽  
Preliminary Ship Design

Modelling of green water ingress into holds of an open-top containership in its preliminary design phase In this paper a method is presented of modelling the green water ingress into holds of open-top containership, which can be useful in the preliminary ship design phase. As a result of the research a mathematical formula which makes it possible to determine a minimum freeboard height with a view of as- low- as- possible occurrence rate of green water ingress into holds at given ship design parameters, was obtained. The research was carried out under assumption of constant ship hull dimensions. The design formula was elaborated by using a method based on a goal-oriented conceptual approach to formulation of design criteria, proposed by IMO. On the basis of the concept a deterministic scenario describing operational conditions of the ship in question, was assumed, and for the conditions the research was performed.

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