The efficiency of transonic aircraft engines depend upon the performance of compressor rotor. To increase
compressor rotors performance flow separation around rotor blades must be delayed and controlled. The aim
was to control the flow separation of blades using suction boundary layer control method.
Rotor blade has been modelled in designing software CATIA and then a suction surface has been created on
blade and then import these geometries to ANSYS-CFX 14.5 for computational analysis of flow around blades.
Suction slot has been applied at the trailing edge of suction surface and Shear stress transport model has been
used for computational analysis.
Two different suction mass flow rates 1 kg/s and 1.5 kg/s have been used here and boundary layer separation
effects have been changed and this could be readily seen that the velocity vectors have reattached, preventing
the boundary layer separation at the suction surface of the blade.
Improving the Hydraulic Efficiency of Centrifugal Pumps through Computational...IJERA Editor
The design and optimization of turbo machine impellers such as those in pumps and turbines is a highly complicated task due to the complex three-dimensional shape of the impeller blades and surrounding devices. Small differences in geometry can lead to significant changes in the performance of these machines. We report here an efficient numerical technique that automatically optimizes the geometry of these blades for maximum performance. The technique combines, mathematical modeling of the impeller blades using non-uniform rational B-spline (NURBS), Computational fluid dynamics (CFD) with Geometry Parameterizations in turbulent flow simulation and the Globalized and bounded Nelder-Mead (GBNM) algorithm in geometry optimization.
Finite Element Analysis of Shaft of Centrifugal PumpIOSR Journals
Centrifugal pump is world one of the oldest water pumping devises. The current work deals study
Shaft of centrifugal pump for static and dynamic analysis. As we know rotodynamic machineries are designed
keenly as there is lot of fluctuation in the loads and speeds. The shaft is analyzed by using finite element analysis
technique for stresses and deflections. The total work is carried out in two stages first stage is static analysis. In
this stage pump shaft is analyzed for stresses and deflection and same results are verified using graphical
integration method. And second for dynamic analysis, in this stage result obtained by static analysis are used to
calculate dynamic forces coming in pump shaft. Again shaft is analyzed in dynamic input condition and results
are verified by using graphical integration method. The software used for the finite element meshing is
HYPERMESH and solver used is RADIOSS. Result values obtained for deflection and stresses are compared in
both cases. Result obtained by graphical method and FEA are nearly similar and are in acceptable limits.
Design and Development of Transonic Axial Flow Compressor Rotor BladeIJERDJOURNAL
Abstract:- This paper is about a new computational fluid dynamics developed for the transonic flow in a compressor rotor. Due to 3-Dimensional blade modification the arrangements satisfying the required boundary condition. Engine compressor towards distorted inflow has to be taken in account which is already in the design phase. Flow separation over the blade surface reduction and elimination can improve better aerodynamic, performance, efficiency and stall margin. NASA transonic rotor tip critical in baseline blade rotor performance energizing the low momentum boundary layer, controlling the inception of stall. A Profile generator are attached on the inner casing of the rotor ahead to the loading edge of the rotor and it is influenced on the overall performance which has been studied.
Numerical Simulation of the Aerodynamic Performance of a H-type Wind Turbine ...Capvidia NV
Wind Turbine Self Starting CFD Simulation with FlowVision This is a nice example for moving bodies. Moment of inertia of turbine is defined and rotation is induced by aerodynamics forces. Simulation results of rotation speed variation during self-starting are in well agreement with the experimental results.
Improving the Hydraulic Efficiency of Centrifugal Pumps through Computational...IJERA Editor
The design and optimization of turbo machine impellers such as those in pumps and turbines is a highly complicated task due to the complex three-dimensional shape of the impeller blades and surrounding devices. Small differences in geometry can lead to significant changes in the performance of these machines. We report here an efficient numerical technique that automatically optimizes the geometry of these blades for maximum performance. The technique combines, mathematical modeling of the impeller blades using non-uniform rational B-spline (NURBS), Computational fluid dynamics (CFD) with Geometry Parameterizations in turbulent flow simulation and the Globalized and bounded Nelder-Mead (GBNM) algorithm in geometry optimization.
Finite Element Analysis of Shaft of Centrifugal PumpIOSR Journals
Centrifugal pump is world one of the oldest water pumping devises. The current work deals study
Shaft of centrifugal pump for static and dynamic analysis. As we know rotodynamic machineries are designed
keenly as there is lot of fluctuation in the loads and speeds. The shaft is analyzed by using finite element analysis
technique for stresses and deflections. The total work is carried out in two stages first stage is static analysis. In
this stage pump shaft is analyzed for stresses and deflection and same results are verified using graphical
integration method. And second for dynamic analysis, in this stage result obtained by static analysis are used to
calculate dynamic forces coming in pump shaft. Again shaft is analyzed in dynamic input condition and results
are verified by using graphical integration method. The software used for the finite element meshing is
HYPERMESH and solver used is RADIOSS. Result values obtained for deflection and stresses are compared in
both cases. Result obtained by graphical method and FEA are nearly similar and are in acceptable limits.
Design and Development of Transonic Axial Flow Compressor Rotor BladeIJERDJOURNAL
Abstract:- This paper is about a new computational fluid dynamics developed for the transonic flow in a compressor rotor. Due to 3-Dimensional blade modification the arrangements satisfying the required boundary condition. Engine compressor towards distorted inflow has to be taken in account which is already in the design phase. Flow separation over the blade surface reduction and elimination can improve better aerodynamic, performance, efficiency and stall margin. NASA transonic rotor tip critical in baseline blade rotor performance energizing the low momentum boundary layer, controlling the inception of stall. A Profile generator are attached on the inner casing of the rotor ahead to the loading edge of the rotor and it is influenced on the overall performance which has been studied.
Numerical Simulation of the Aerodynamic Performance of a H-type Wind Turbine ...Capvidia NV
Wind Turbine Self Starting CFD Simulation with FlowVision This is a nice example for moving bodies. Moment of inertia of turbine is defined and rotation is induced by aerodynamics forces. Simulation results of rotation speed variation during self-starting are in well agreement with the experimental results.
Numerical Investigation of Single Stage of an Axial Flow Compressor for Effec...IJERA Editor
In present work, a compressor configuration is taken from literature which will be studied for aspect ratio (ratio between length of blade to chord length) influence over performance. Performance in the sense is pressure ratio of compressor. The aspect ratio of the blade is an important parameter and has a strong influence on the performance of axial flow compressor. There are so many literatures available on influence of design parameters of axial flow compressor over its performance. Few literatures only are available for effects of aspect ratio of blade over performance of compressor. A study is proposed to be carried out to verify the effect of aspect ratio on the performance of single stage subsonic compressor through ANSYS-CFX software. The analysis will be carried out for the constant tip diameter of the compressor rotor blade having an aspect ratio 1, 2 and 3 and to obtain the pressure loss and flow parameters of the compressor stage. Further increase in aspect ratio will lead to structural problem of compressor. Therefore, there will be optimum aspect ratio between 2 and 3. Simulation will be conducted to aspect ratios of 2.1, 2.2, 2.3, 2.4, 2.5, 2.6, 2.7, 2.8 and 2.9 to find optimum ratio using ANSYS-CFX commercial CFD software.
Optimization of design of mixed flow centrifugal pump impeller using cfdeSAT Journals
Abstract
Centrifugal pumps are widely used hydraulic machines, irrespective of the fact that their performance is generally not very good. So, turning them into more efficient machines is quite a challenge. The performance of a centrifugal pump is highly dependent on its geometrical parameters and its vane profile. In order to analyze the flow through complex systems like centrifugal pumps, Computation fluid dynamics (CFD) has been used. This work aims to study the performance analysis of a centrifugal mixed flow pump designed to deliver 0.25 m3/s of water with a head of 20 m at a speed of 1450 rpm using ANSYS CFX (ver.14.0). PTC Creo (ver. 2.0) has been used to model the pump unit. The performance of the pump was first determined using the existing vane angles and thickness of the blade then, the inlet vane angle, the outlet vane angle along with the thickness of the blade has been varied to analyze the pump’s performance . The results show that for an initial inlet angle 21.08˚, outlet angle 16.28˚ and blade thickness as 10mm, the efficiency of the pump was 84%. However, the efficiency of pump rises to 89.19% for the optimized angles and blade thickness.
Experimental Investigations to Study the Air Flow Patterns on the Headlight D...IJERA Editor
This paper presents some experimental investigations to study the air flow patterns on the headlight domes of different two wheelers (HERO HONDA PASSION PLUS and BAJAJ PULSAR) which influence the stability of the vehicle. The pressure distribution over the surface of the profile and the drag force are to be determined for various headlight dome orientations. This study helps in suggesting the suitable headlight dome profile that may reduce the drag force and effect of turbulence which in turn leads to the increase of vehicle stability. The results obtained during the simulation are to be validated by conducting the experiments on the scale down model of the headlight dome of HERO HONDA PASSION PLUS using Wind Tunnel test rig. The Computational Fluid Dynamics (CFD) tool was used to simulate the air flow pattern on the headlight dome in which boundary layer separation doesn’t exist. The results obtained from the simulation are to be compared with the experimental results from the wind tunnel and the variation is to be found and that should be in the acceptable limit.
FLUID FLOW ANALYSIS OF CENTRIFUGAL FAN BY USING FEMIAEME Publication
The forward backward curved (mixed) Centrifugal fan 630 has been analyzed aerodynamically for compare experimental results with simulation results by using ANSYS FLUENT (Finite Element Analysis Software). The material of the fan impeller was specified as ALUMINIUM. Boundary conditions on the Centrifugal fan-630 are taken from the reference. The flow distribution across the fan is obtained. The maximum static pressure at the inlet is known and the pressure distributions across the blade are obtained accordingly. The obtained results are compared with Experimental results is discussed. In final recommended the design of the centrifugal fan and results are tabulated. It’s observed that simulation results are nearer to the experimental results.
Assessment of Flow Control using Passive Devices around Bluff BodiesAnuragSingh1049
This article presents a review study on the experimental investigation of aerodynamic force on a car like bluff bodies along with the simulations using different turbulence models used in CFD (Computational Fluid Dynamics). The aim of the study is to find a useful method for the better design of a car body. It was observed that combination of wind tunnel experiments and CFD computation can lead to better aerodynamic design. Significant reduction in coefficient of the lift and drag for a car model were found when a more streamlined body design was adopted. Appropriate change in the slant angle for the car body can significantly reduce the fuel consumption. Also, the use of simulations in combination with the experimental observations helps in predicting the flow behavior more accurately.
Performance prediction of a turboshaft engine by using of one dimensional ana...ijmech
Performance estimation of the axial flow gas turbines under variety of operating conditions like different speeds and pressure ratios has been hampered by lack of reliable experimental data and experiments cost.Simulation of gas turbine is a simple way to reduce testing costs and complexity.One-dimensional (1D).Simulation is a simple, fast and accurate method for performance prediction of turbine with different geometries. In this approach, inlet flow conditions and turbine geometry are known and by considering loss model, the turbine performance characteristics are predicted. In following work, that is based on one dimensional modelling method, after the presentation of solution algorithm by trial and error method and introduction of different loss models for modelling, this method were examined for a turbo shaft engine and
compared with experimental results. Comparison of the results with experimental data shows so good adaptation. Also according to these results, Kacker and Okapuu’s developed model gave the closest results to the reference data.
International Journal of Engineering Research and Applications (IJERA) aims to cover the latest outstanding developments in the field of all Engineering Technologies & science.
International Journal of Engineering Research and Applications (IJERA) is a team of researchers not publication services or private publications running the journals for monetary benefits, we are association of scientists and academia who focus only on supporting authors who want to publish their work. The articles published in our journal can be accessed online, all the articles will be archived for real time access.
Our journal system primarily aims to bring out the research talent and the works done by sciaentists, academia, engineers, practitioners, scholars, post graduate students of engineering and science. This journal aims to cover the scientific research in a broader sense and not publishing a niche area of research facilitating researchers from various verticals to publish their papers. It is also aimed to provide a platform for the researchers to publish in a shorter of time, enabling them to continue further All articles published are freely available to scientific researchers in the Government agencies,educators and the general public. We are taking serious efforts to promote our journal across the globe in various ways, we are sure that our journal will act as a scientific platform for all researchers to publish their works online.
Electrical, Electronics and Computer Engineering,
Information Engineering and Technology,
Mechanical, Industrial and Manufacturing Engineering,
Automation and Mechatronics Engineering,
Material and Chemical Engineering,
Civil and Architecture Engineering,
Biotechnology and Bio Engineering,
Environmental Engineering,
Petroleum and Mining Engineering,
Marine and Agriculture engineering,
Aerospace Engineering.
Numerical Investigation of Single Stage of an Axial Flow Compressor for Effec...IJERA Editor
In present work, a compressor configuration is taken from literature which will be studied for aspect ratio (ratio between length of blade to chord length) influence over performance. Performance in the sense is pressure ratio of compressor. The aspect ratio of the blade is an important parameter and has a strong influence on the performance of axial flow compressor. There are so many literatures available on influence of design parameters of axial flow compressor over its performance. Few literatures only are available for effects of aspect ratio of blade over performance of compressor. A study is proposed to be carried out to verify the effect of aspect ratio on the performance of single stage subsonic compressor through ANSYS-CFX software. The analysis will be carried out for the constant tip diameter of the compressor rotor blade having an aspect ratio 1, 2 and 3 and to obtain the pressure loss and flow parameters of the compressor stage. Further increase in aspect ratio will lead to structural problem of compressor. Therefore, there will be optimum aspect ratio between 2 and 3. Simulation will be conducted to aspect ratios of 2.1, 2.2, 2.3, 2.4, 2.5, 2.6, 2.7, 2.8 and 2.9 to find optimum ratio using ANSYS-CFX commercial CFD software.
Optimization of design of mixed flow centrifugal pump impeller using cfdeSAT Journals
Abstract
Centrifugal pumps are widely used hydraulic machines, irrespective of the fact that their performance is generally not very good. So, turning them into more efficient machines is quite a challenge. The performance of a centrifugal pump is highly dependent on its geometrical parameters and its vane profile. In order to analyze the flow through complex systems like centrifugal pumps, Computation fluid dynamics (CFD) has been used. This work aims to study the performance analysis of a centrifugal mixed flow pump designed to deliver 0.25 m3/s of water with a head of 20 m at a speed of 1450 rpm using ANSYS CFX (ver.14.0). PTC Creo (ver. 2.0) has been used to model the pump unit. The performance of the pump was first determined using the existing vane angles and thickness of the blade then, the inlet vane angle, the outlet vane angle along with the thickness of the blade has been varied to analyze the pump’s performance . The results show that for an initial inlet angle 21.08˚, outlet angle 16.28˚ and blade thickness as 10mm, the efficiency of the pump was 84%. However, the efficiency of pump rises to 89.19% for the optimized angles and blade thickness.
Experimental Investigations to Study the Air Flow Patterns on the Headlight D...IJERA Editor
This paper presents some experimental investigations to study the air flow patterns on the headlight domes of different two wheelers (HERO HONDA PASSION PLUS and BAJAJ PULSAR) which influence the stability of the vehicle. The pressure distribution over the surface of the profile and the drag force are to be determined for various headlight dome orientations. This study helps in suggesting the suitable headlight dome profile that may reduce the drag force and effect of turbulence which in turn leads to the increase of vehicle stability. The results obtained during the simulation are to be validated by conducting the experiments on the scale down model of the headlight dome of HERO HONDA PASSION PLUS using Wind Tunnel test rig. The Computational Fluid Dynamics (CFD) tool was used to simulate the air flow pattern on the headlight dome in which boundary layer separation doesn’t exist. The results obtained from the simulation are to be compared with the experimental results from the wind tunnel and the variation is to be found and that should be in the acceptable limit.
FLUID FLOW ANALYSIS OF CENTRIFUGAL FAN BY USING FEMIAEME Publication
The forward backward curved (mixed) Centrifugal fan 630 has been analyzed aerodynamically for compare experimental results with simulation results by using ANSYS FLUENT (Finite Element Analysis Software). The material of the fan impeller was specified as ALUMINIUM. Boundary conditions on the Centrifugal fan-630 are taken from the reference. The flow distribution across the fan is obtained. The maximum static pressure at the inlet is known and the pressure distributions across the blade are obtained accordingly. The obtained results are compared with Experimental results is discussed. In final recommended the design of the centrifugal fan and results are tabulated. It’s observed that simulation results are nearer to the experimental results.
Assessment of Flow Control using Passive Devices around Bluff BodiesAnuragSingh1049
This article presents a review study on the experimental investigation of aerodynamic force on a car like bluff bodies along with the simulations using different turbulence models used in CFD (Computational Fluid Dynamics). The aim of the study is to find a useful method for the better design of a car body. It was observed that combination of wind tunnel experiments and CFD computation can lead to better aerodynamic design. Significant reduction in coefficient of the lift and drag for a car model were found when a more streamlined body design was adopted. Appropriate change in the slant angle for the car body can significantly reduce the fuel consumption. Also, the use of simulations in combination with the experimental observations helps in predicting the flow behavior more accurately.
Performance prediction of a turboshaft engine by using of one dimensional ana...ijmech
Performance estimation of the axial flow gas turbines under variety of operating conditions like different speeds and pressure ratios has been hampered by lack of reliable experimental data and experiments cost.Simulation of gas turbine is a simple way to reduce testing costs and complexity.One-dimensional (1D).Simulation is a simple, fast and accurate method for performance prediction of turbine with different geometries. In this approach, inlet flow conditions and turbine geometry are known and by considering loss model, the turbine performance characteristics are predicted. In following work, that is based on one dimensional modelling method, after the presentation of solution algorithm by trial and error method and introduction of different loss models for modelling, this method were examined for a turbo shaft engine and
compared with experimental results. Comparison of the results with experimental data shows so good adaptation. Also according to these results, Kacker and Okapuu’s developed model gave the closest results to the reference data.
International Journal of Engineering Research and Applications (IJERA) aims to cover the latest outstanding developments in the field of all Engineering Technologies & science.
International Journal of Engineering Research and Applications (IJERA) is a team of researchers not publication services or private publications running the journals for monetary benefits, we are association of scientists and academia who focus only on supporting authors who want to publish their work. The articles published in our journal can be accessed online, all the articles will be archived for real time access.
Our journal system primarily aims to bring out the research talent and the works done by sciaentists, academia, engineers, practitioners, scholars, post graduate students of engineering and science. This journal aims to cover the scientific research in a broader sense and not publishing a niche area of research facilitating researchers from various verticals to publish their papers. It is also aimed to provide a platform for the researchers to publish in a shorter of time, enabling them to continue further All articles published are freely available to scientific researchers in the Government agencies,educators and the general public. We are taking serious efforts to promote our journal across the globe in various ways, we are sure that our journal will act as a scientific platform for all researchers to publish their works online.
Electrical, Electronics and Computer Engineering,
Information Engineering and Technology,
Mechanical, Industrial and Manufacturing Engineering,
Automation and Mechatronics Engineering,
Material and Chemical Engineering,
Civil and Architecture Engineering,
Biotechnology and Bio Engineering,
Environmental Engineering,
Petroleum and Mining Engineering,
Marine and Agriculture engineering,
Aerospace Engineering.
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
Numerical Simulation of a Centrifugal CompressorIJERA Editor
In this paper, the tip clearance effects on flow field of a low speed centrifugal compressor without and with partial shroud (PS) fitted on to the rotor blade tip at three values of tip clearance, viz. = 2.2%, 5.1% and 7.9% of rotor blade height at the exit at three flow coefficients, namely, = 0.18, 0.28, and 0.34, was studied. Based on the theory of computational fluid dynamics (CFD), performance curves and parameter distributions of the compressor were obtained from the 3-D numerical simulation by using ANSYS CFX 15.0. The centrifugal compressor in aerodynamic requirement is that edge velocities along the impeller channel passage surfaces like hub, shroud, pressure and suction surfaces vary smoothly without sudden decelerations, which cause flow separation leading to losses. Using the periodic boundaries and defined flow conditions at inflow / exit flow and blade rotations, the turbulent viscous flow between blade channels are computed. The efficiency related parameters using average quantities, besides flow pattern in terms of velocities, streamlines and pressure distribution on blade surfaces are graphically interpreted. An attempt is also made to study the influence of pressure loads on structural deformations in the chosen blade profile. This paper highlights aero-mechanical features of centrifugal impeller obtained from several numerical simulations, which are expected to provide a sound basis for further investigations. Keywords: Centrifugal compressor, Fl
Design optimization of an axial flow compressor for industrial gas turbineeSAT Publishing House
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology
Car’s Aerodynamic Characteristics at High Speed Influenced by Rear SpoilerIJRES Journal
The factors affect the rear spoiler’s aerodynamics characteristics are cross-sectional shape, chord length and angle of attack. By changing the three factors that can change the state of the car flow field. Determine the main body size, build models by Solidworks . Use Hypermesh to mesh, increase the number of grid near the body especially at the rear spoiler. Use Fluent for fluid analysis to get the values of aerodynamic lift coefficient CL (at 120km / h) based on orthogonal experiments. After calculating, obtain significance order of factors can obtain the best rear spoiler shape, helping to optimize the automotive styling quickly, improve the car's power and economy, ease the new car quickly seize the market.
Design Optimization and Analysis of a Steam Turbine Rotor GroovesIOSR Journals
A large variety of turbo-machinery rotor groove geometries are used in industry. However, there is
no specific attempt made to compare them on the basis of performance. This paper provides an attempt to fill
that gap aiming to find an optimum geometry. The main objective of the investigations is to reduce fillet stress
concentration factor and associated deformations. The present work carries out the design modification of fillet
of a Steam Turbine Rotor. Finite Element Analysis is performed using ANSYS Workbench that is used to
determine the fillet stresses effectively to modify the blade rotor grooves. The low pressure steam turbine rotor
blades have usually a history of stress failure. They suffer from tensile and bending stresses partly due to the
centrifugal force as a result of high rotational speeds and partly due to high pressure, temperature and speed
steam loading. The centrifugal force is one of the problems that face the designers of turbine blades especially
the long ones. The designer always aims at reducing these stresses. One way to do so is by the reduction of
stress concentration factor which takes place between the rotor and its groove. That is to make the rotor blade
of variable cross section instead of straight. This paper presents the method of reducing stress concentration
factor as well as reduction in the deformation of the rotor
Similar to Flow Modification over Rotor Blade with Suction Boundary Layer Control Technique (20)
Immunizing Image Classifiers Against Localized Adversary Attacksgerogepatton
This paper addresses the vulnerability of deep learning models, particularly convolutional neural networks
(CNN)s, to adversarial attacks and presents a proactive training technique designed to counter them. We
introduce a novel volumization algorithm, which transforms 2D images into 3D volumetric representations.
When combined with 3D convolution and deep curriculum learning optimization (CLO), itsignificantly improves
the immunity of models against localized universal attacks by up to 40%. We evaluate our proposed approach
using contemporary CNN architectures and the modified Canadian Institute for Advanced Research (CIFAR-10
and CIFAR-100) and ImageNet Large Scale Visual Recognition Challenge (ILSVRC12) datasets, showcasing
accuracy improvements over previous techniques. The results indicate that the combination of the volumetric
input and curriculum learning holds significant promise for mitigating adversarial attacks without necessitating
adversary training.
NO1 Uk best vashikaran specialist in delhi vashikaran baba near me online vas...Amil Baba Dawood bangali
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Quality defects in TMT Bars, Possible causes and Potential Solutions.PrashantGoswami42
Maintaining high-quality standards in the production of TMT bars is crucial for ensuring structural integrity in construction. Addressing common defects through careful monitoring, standardized processes, and advanced technology can significantly improve the quality of TMT bars. Continuous training and adherence to quality control measures will also play a pivotal role in minimizing these defects.
Event Management System Vb Net Project Report.pdfKamal Acharya
In present era, the scopes of information technology growing with a very fast .We do not see any are untouched from this industry. The scope of information technology has become wider includes: Business and industry. Household Business, Communication, Education, Entertainment, Science, Medicine, Engineering, Distance Learning, Weather Forecasting. Carrier Searching and so on.
My project named “Event Management System” is software that store and maintained all events coordinated in college. It also helpful to print related reports. My project will help to record the events coordinated by faculties with their Name, Event subject, date & details in an efficient & effective ways.
In my system we have to make a system by which a user can record all events coordinated by a particular faculty. In our proposed system some more featured are added which differs it from the existing system such as security.
Cosmetic shop management system project report.pdfKamal Acharya
Buying new cosmetic products is difficult. It can even be scary for those who have sensitive skin and are prone to skin trouble. The information needed to alleviate this problem is on the back of each product, but it's thought to interpret those ingredient lists unless you have a background in chemistry.
Instead of buying and hoping for the best, we can use data science to help us predict which products may be good fits for us. It includes various function programs to do the above mentioned tasks.
Data file handling has been effectively used in the program.
The automated cosmetic shop management system should deal with the automation of general workflow and administration process of the shop. The main processes of the system focus on customer's request where the system is able to search the most appropriate products and deliver it to the customers. It should help the employees to quickly identify the list of cosmetic product that have reached the minimum quantity and also keep a track of expired date for each cosmetic product. It should help the employees to find the rack number in which the product is placed.It is also Faster and more efficient way.
Student information management system project report ii.pdfKamal Acharya
Our project explains about the student management. This project mainly explains the various actions related to student details. This project shows some ease in adding, editing and deleting the student details. It also provides a less time consuming process for viewing, adding, editing and deleting the marks of the students.
About
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
• Remote control: Parallel or serial interface.
• Compatible with MAFI CCR system.
• Compatible with IDM8000 CCR.
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
• Easy in configuration using DIP switches.
Technical Specifications
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
Key Features
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
• Remote control: Parallel or serial interface
• Compatible with MAFI CCR system
• Copatiable with IDM8000 CCR
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
Application
• Remote control: Parallel or serial interface.
• Compatible with MAFI CCR system.
• Compatible with IDM8000 CCR.
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
• Easy in configuration using DIP switches.
Vaccine management system project report documentation..pdfKamal Acharya
The Division of Vaccine and Immunization is facing increasing difficulty monitoring vaccines and other commodities distribution once they have been distributed from the national stores. With the introduction of new vaccines, more challenges have been anticipated with this additions posing serious threat to the already over strained vaccine supply chain system in Kenya.
Forklift Classes Overview by Intella PartsIntella Parts
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CFD Simulation of By-pass Flow in a HRSG module by R&R Consult.pptxR&R Consult
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CFD Simulation of By-pass Flow in a HRSG module by R&R Consult.pptx
Flow Modification over Rotor Blade with Suction Boundary Layer Control Technique
1. Navneet Kumaret al. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 6, Issue 6, ( Part -6) June 2016, pp.01-05
www.ijera.com 1|P a g e
Flow Modification over Rotor Blade with Suction Boundary
Layer Control Technique
Navneet Kumar
(Department of Aerospace Engineering, Indian Institute of Technology, Kanpur-16)
ABSTRACT
The efficiency of transonic aircraft engines depend upon the performance of compressor rotor. To increase
compressor rotors performance flow separation around rotor blades must be delayed and controlled. The aim
was to control the flow separation of blades using suction boundary layer control method.
Rotor blade has been modelled in designing software CATIA and then a suction surface has been created on
blade and then import these geometries to ANSYS-CFX 14.5 for computational analysis of flow around blades.
Suction slot has been applied at the trailing edge of suction surface and Shear stress transport model has been
used for computational analysis.
Two different suction mass flow rates 1 kg/s and 1.5 kg/s have been used here and boundary layer separation
effects have been changed and this could be readily seen that the velocity vectors have reattached, preventing
the boundary layer separation at the suction surface of the blade.
Keywords – Boundary Layer, Compressor, Pressure ratio, Rotor blade, Suction
I. INTRODUCTION
There are various devices and methods
available today to prevent compressor flow
instabilities. Some of the methods are casing
treatment, tiny grooves or slots made onendwall etc.
and these methods have been employed to
compressor rotor blade in the late 1970s’.
In Transonic flow which is partly high
subsonic and low supersonic geometry of
compressor rotor blade is very important due to
occurrence of shock performance of compressor
depends upon rotor blade. Shock causes separation
which increases losses and as a result efficiency of
engine decreases therefore many methods like
adding plasma actuating devices on the trailing edge
of blade, Boundary layer control by suction etc. have
been developed to delay or prevent separation.
In the present study the flow field of transonic
compressor rotor has been numerically simulated to
clarify the mechanism of Boundary layer control by
suction.
1.1 Compressor Rotor specifications
Rotor which has been used here was a low aspect
ratio transonic axial flow fan having more than
twenty blades. The design pressure ratio was nearly
about 1.68, mass flow rate was 33 kg/s, having
rotational speed of 16000 RPM and tip speed was
425 m/s. The solidity of rotor fan varies from 3.1 at
the hub and 1.29 at the tip.
1.2 Boundary layer and Boundary layer control
method
Boundary layer is the region where mass,
momentum, heat transfers are felt, viscosity effect is
significant here and due to these effects flow is
retarded and cause separation. Flow separation
depends on this layer and parameters like entropy
layer, viscous layer, pressure and temperature
depends on separation therefore this layer play key
role in deciding performance. To increase
performance separation must be prevented or
delayed to get desired flow parameters.
To overcome the losses caused by
separation and to achieve desire flow parameters
boundary layer control methods are used. In this
paper suction hole has been created on the rotor
blade surface in such a manner that this will be used
to reenergize the low energy fluid so that the
separation point shifts and reduces the no slip
condition.
1.3 Equation
Isentropic Efficiency:-
𝜂 =
𝑃𝑅
𝛾−1
𝛾 −1
𝑇2
𝑇1−1
……(1)
In the “equation 1” PR is the pressure ratio and 𝛾 is
the specific heat ratio for air which has the
numerical value of 1.4. 𝑇2 and𝑇1 are the total
temperatures of outlet and inlet respectively.
RESEARCH ARTICLE OPEN ACCESS
2. Navneet Kumaret al. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 6, Issue 6, ( Part -6) June 2016, pp.01-05
www.ijera.com 2|P a g e
II. METHODOLOGY
2.1 Modeling
Designing software CATIA has been used
for the modelling of blades of compressor. Four
points were joined together to form one surface and
these points were taken on the basis of literature
survey of previous technical paper. Due to
complexity of curve of blade (it is twisted from hub
to tip) modelling of compressor blade was not an
easy job to do. If we do not have coordinates of
point then modelling of rotor blade was not possible
in this software and once coordinates of points were
decided then by connecting all the points blade
surfaces has been formed and geometric model of
blade was ready and after this outer walls and casing
hubs has been designed in this designing software.
Figure1 modelling of Rotor blades
Table 1 Important Parameters of Model in mm
Maximum Chord length – 143
Maximum Span-- 250
Inlet Diameter-- 202
Outlet Diameter-- 147
Tip Clearance-- 4.25
There were more than twenty blades in
rotor and no of elements for each blade was very
large which would take too much computational
time and cost. To overcome this our model has been
restricted to single blade and computational analysis
has been done on single blade model.
Figure2 single blade model with hub and casing
Modelling of blade geometry with suction
could be done by creating one suction surface on the
blade and creating suction hole at the Trailing edge
of the blade which has beens shown in the next
figure.
Figure3 rotor blade with suction surface and hole
2.2Mesh Creation and grid parameters
2.2.1Grid generation without Suction
Creation of mesh is very important in
computational simulation of fluid flow. If mesh is
not of good quality then this may affect our results.
Two types of mesh has been used for our geometry
one was Quad dominant and other one was volume
tetra or mixed type mesh and these were obtained by
shell meshing and patch dependent methods
respectively.
When geometry has been imported from
CATIA to ICEM CFD 14.5 then parts have been and
each part was assigned a name. After creation of
parts then geometry should be repaired by providing
tolerance to 0.1 ( the tolerance of 0.1 was given
according to length of the smallest component in the
model) and then apply and then delete surfaces have
been selected and delete overlapping surface and any
hole in geometry and once geometry has been
repaired then this should be moved for meshing.
Repairing of geometry was required beacuse in
importing geometry from CATIA to ICEM some
surfaces were overlapped or lost or some holes have
been created in geometry and this would affect the
meshing and if our meshing was not proper then we
were not able to get result. After this body should be
created by selecting two points diagonally.By doing
this fine mesh could be created on the blade surface
than the casing and outer walls.
For considering boundary layer effects on the flow
height was kept fixed and number of prism layers
were calculated using Y+ calculators.
3. Navneet Kumaret al. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 6, Issue 6, ( Part -6) June 2016, pp.01-05
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Figure4parameters of part mesh setup
Once the global mesh parameters has been
defined then part mesh setup needs to be defined
which has been shown in the above fig. In the part
mesh setup different element sizes has been
provided through which coarsen mesh on the edge of
blade should be possible. After defining all the
parameters then create prism layer and then apply
compute for generating meshing grids.
Figure5 meshing grids of blade and outer walls and
casing
2.2.2 Grid generation with suction
In this geometry one new part named as
suction layer was created and now follow all the
steps which has been done previously to form mesh .
Figure6 meshing grid of blade with suction
2.3 Boundary Conditions for CFD analyis
Computational Fluid dynamics could be
used to analyze and solvethe model flow assosciated
with the fluid by usning numerical methods.
Different softwares are available today for CFD
analysis in this study ANSYS-CFX is used for this.
2.3.1 CFX-pre setup for Model without suction
surface
The settings for CFX- Pre used were based
on the units of the mesh imported.
The parameters for the mesh units in mm were:-
Basic Settings
Machine Type : Axial Compressor
Rotation Axis : z
Component type
Type : Rotating
Value -16043 [RPM]
Tip clearance at shroud : yes
Fluid :-- Air Ideal Gas
Analysis Type : -- Steady State
Model data :
Reference Pressure :- 0 (Zero) Pa
Heat Transfer :- Total Energy
Turbulence :- Shear stress Transport
Wall Functions :- Automatic and compressible
high speed heat transfer model
Inflow/Outflow boundary templates: P-total
inlet P-static outlet
Inflow Boundary condition:
Mass and Momentum :- Static Frame Total
Pressure
Relative Pressure ( P- Total) :- 101325 Pa
Flow direction :- Normal to the boundary
Static Frame Total temperature :- 288.2 K
Outlet Boundary condition:
Mass and Momentum :- Static Pressure and
mention pressure as 114500 Pa
Solver Parameter :
Advection Scheme :- High Resolution
Time Scale Control :- Auto Timescale
Length Scale :- Conservative
Maximum Timescale :- 0.000001
Convergence Residual Criteria:- MAX Type
and Target as 0.00001
The parameters for the mesh units in cm are:-
Basic Settings
Machine Type : Axial Compressor
Rotation Axis : z
Component type
Type : Rotating
Value -3600 [RPM]
Tip clearance at shroud : yes
Fluid :-- Air Ideal Gas
Analysis Type : -- Steady State
Model data :
Reference Pressure :- 0 (Zero) Pa
Heat Transfer :- Total Energy
Turbulence :- Shear stress Transport
Wall Functions :- Automatic and compressible
high speed heat transfer model
4. Navneet Kumaret al. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 6, Issue 6, ( Part -6) June 2016, pp.01-05
www.ijera.com 4|P a g e
Inflow/Outflow boundary templates: P-total
inlet P-static outlet
Inflow Boundary condition:
Mass and Momentum :- Static Frame Total
Pressure
Relative Pressure ( P- Total) :- 101325 Pa
Flow direction :- Normal to the boundary
Static Frame Total temperature :- 288.2 K
Outlet Boundary condition:
Mass and Momentum :- Static Pressure and
mention pressure as 114500 Pa
Solver Parameter :
Advection Scheme :- High Resolution
Time Scale Control :- Auto Timescale
Length Scale :- Conservative
Maximum Timescale :- 0.000001
Convergence Residual Criteria:-MAX Type
and Target as 0.00001
2.3.2 CFX-pre setup for Model with suction
surface
The suction boundary layer was applied as
outlet and the two conditions were put up on it
according to the two mass flow rates selected. The
mass flow rates for the suction boundary layer were
put up according to the literature review which states
that the aspiration of 2% mass flow rate was most
effective in controlling the boundary layer
separation. So mass flow rates of 1Kg/s and 1.5Kg/s
were used.
The parameters for the problem applied were:-
Basic Settings
Machine Type : Axial Compressor
Rotation Axis : z
Component type
Type : Rotating
Value -16043 [RPM]
Tip clearance at shroud : yes
Fluid :-- Air Ideal Gas
Analysis Type : -- Steady State
Model data :
Reference Pressure :- 0 (Zero) Pa
Heat Transfer :- Total Energy
Turbulence :- Shear stress Transport
Wall Functions :- Automatic and compressible
high speed heat transfer model
Inflow/Outflow boundary templates: P-total
inlet P-static outlet
Inflow Boundary condition:
Mass and Momentum :- Static Frame Total
Pressure
Relative Pressure ( P- Total) :- 101325 Pa
Flow direction :- Normal to the boundary
Static Frame Total temperature :- 288.2 K
Outlet Boundary condition:
Mass and Momentum :- Static Pressure and
mention pressure as 114500 Pa
Suction:
Mass and Momentum :- Outlet and mass flow
rate of 1Kg/s or 1.5 Kg/s
Solver Parameter :
Advection Scheme :- High Resolution
Time Scale Control :- Auto Timescale
Length Scale :- Conservative
Maximum Timescale :- 0.000001
Convergence Residual Criteria:- MAX Type
and Target as 0.00001
2.3.3 CFX solver manager
The output file generated in CFX-pre was
the input file for this part and this uses graphical
interface method for CFD calculations. Double
precision was selected because it gives more
accurate numerical solution but when this method
was used computer memory and grid size was also
doubled when this solver execute the file.
2.3.4 CFX-post Processor
The output of the simulation or the result
file was then loaded in this where the flow can be
analyzed. When the results were initialized
thermodynamic properties can also be extracted
from optimization process therefore expression of
isentropic efficiency and pressure ratio has been also
created in expression tab of CFD-Post.
III. Results and Discussion
Above defined models were analyzed in
CFX-post processor. First model with no boundary
layer control method was analyzed and results were
obtained as velocity vectors at various span locations
for two models with changed rpm and length units.
Figure7 velocity vectors at 25% span
Figure8 velocity vectors at 45% span
5. Navneet Kumaret al. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 6, Issue 6, ( Part -6) June 2016, pp.01-05
www.ijera.com 5|P a g e
Figure9 velocity vectors at 85% span
The above three fig. shows that how the
flow separation occurs when there was no suction
surface present in the model and this was analyzed
for model having two different length units but the
results were similar. At the point where flow
separation occurredcolor changed from orange to
green and among three figures boundary layer
effects could be seen as dominant in the fig. 7 near
quarter of span where some strong vortex are also
forming.
Due to some computational error and single
blade model consideration and its range confined to
60 degrees pressure ratio comes nearly about 1.6.
According to the results obtained here we
need to develop some steps to control boundary
layer separation and to achieve this suction method
was selected here.
In the suction method a suction hole was
created at the trailing edge of the suction surface and
to obtain results two mass flow rates (1 kg/s and 1.5
kg/s) has been used.
Figure10 suction method velocity vectors at 25%
span
Figure11 suction method velocity vectors at 45%
span
Figure12 suction method velocity vectors at 85%
span
Above three fig. were showing the results
of flow over blade using suction surface for two
different mass flow rates.
IV. CONCLUSION
From the results obtained for flow with and
without suction method, it was clear that flow
separation has been delayed by the use of suction
surface. Boundary layer effects were dominant near
quarter chord span of blade and some strong vortex
were also seen when suction surface has not been
used but when this control method has been used it
would reenergize the low energy fluid to delay
separation and also very weak vortex were observed
and as a result pressure ratio was observed as 1.652
and increment in pressure ratio has been found to be
as 0.052.
ACKNOWLEDGEMENTS
Author would like to thank university for
providing computational facilities and colleagues for
their continuous support.
REFERENCES
Journal Papers:
[1]. Y. Ito, T. Watanabe and T. Himeno, Effect
of Endwall Countering on Flow Instability
of Transonic Compressor, International
Journal of Gas Turbine, Propulsion and
Power system, 2(1), 2008.
[2]. Abate, Giada, Aerodynamic optimization of
transonic axial compressor rotor, Journal of
Propulsion and Power, 54(5), 2003, 41-55.
[3]. Benini and Ernesto, Three dimensional
multi objective design optimization of a
transonic Aerodynamic optimization of
transonic compressor rotor, International
Journal of Gas Turbine, Propulsion and
Power System, 54(5), 2004.
Theses:
[4]. A. Sarkar, B. Singla and N. Kumar, CFD
analysis of Rotor 67 Blades, University of
Petroleum and Energy Studies, Dehradun,
India, 2015.
Proceeding Papers:
[5]. Navneet Kumar, CFD analysis of rotor
blade with and without boundary layer
control technique, proc. 6th
International
and 43rd
National Conf. on Fluid
Mechanics and Fluid Power, Allahabad,
India, 2016.