Chapter three. Two-dimensional Cascades. Laith Batarseh
|
|
- Eustace Rogers
- 5 years ago
- Views:
Transcription
1 Chapter three Two-dimensional Cascades Laith Batarseh
2 Turbo cascades The linear cascade of blades comprises a number of identical blades, equally spaced and parallel to one another cascade tunnel low-speed, operating in the range m/s high-speed, for the compressible flow range of testing
3 Blade nomenclature Camber line function, y Camber line Thickness, t Maximum camber, b Leading edge Trailing edge Chord line
4 Cascade nomenclature Stagger angle Space Blade entry angle Camber angle Blade exit angle
5 Useful parameter Camber line shape: mainly, circular or parabolic arc Type of thickness distribution: (t(x)) also, the following ratios Space chord ratio (s/l) t max l b l a l α 1 and α 2 Camber angle (θ =α 1 - α 2 ) Stagger angle [ξ=½(α 1 + α 2 )]
6 Cascade forces Two-dimensional Cascades
7 Cascade forces Applying the principle of continuity to a unit depth of span and noting the assumption of incompressibility, yields The momentum equation applied in the x and y directions with constant axial velocity gives,
8 Energy losses loss in total pressure
9 Energy losses A non-dimensional form pressure rise coefficient C p and a tangential force coefficient C f
10 Lift and drag Lift Drag
11 Lift and drag Lift and drag coefficients
12 Lift and drag Two-dimensional Cascades
13 Efficiency of a compressor cascade Assuming a constant lift drag ratio and differentiated with respect α m to m to give the optimum mean flow angle for maximum efficiency
14 Efficiency of a compressor cascade Howell (1945)
15 Compressor cascade performance Howell (1942) Normal design Condition Twice the min total loss (stall)
16 Compressor cascade performance Stall separation fluid deflection incidence stall point is arbitrarily specified as the incidence at which the total pressure loss is twice the minimum loss in total pressure stall is characterized (at positive incidence) by the flow separating from the suction side of the blade surfaces Losses profile losses (friction losses): Secondary losses (force): Y s Y p C Ds C DP 1 c 2 1 c
17 Compressor cascade performance Losses profile losses (friction losses): Secondary losses (force): Y s Y p C Ds C DP 1 c 2 1 c Annulus losses : Y a C Da 1 c where s, H are the blade pitch and blade length respectively
18 Losses Compressor cascade performance Y a C Da 1 c Y s C Ds 1 c Y p C DP 1 c gain input input losses input Y 1 K. E Tangential velocity
19 Compressor cascade performance Compressor cascade correlations Many experimental investigations have confirmed that the efficient performance of compressor cascade blades is limited by the growth and separation of the blade surface boundary layers. factors which can influence the growth of the blade surface boundary layers: surface velocity distribution Reynolds number inlet Mach number free-stream turbulence Unsteadiness surface roughness. Howell use the deflection (δ = α 2 α 2 ) to correlate the designed performance. We give these parameter the superscript (*) The designed (nominal) parameters are found using Howell figures mentioned before
20 Compressor cascade performance Compressor cascade correlations The correlation of Howell where n=0.5 for compressor cascades and n =1 for compressor inlet guide vanes δ* is relaxation factor added to the first assumption of α 2.
21 Compressor cascade performance Assume α* 2 = 20 o m = 0.27 = 8.1 o Assume better value of α* 2 = 28.1 o m = δ* = 8.6 α* 2 = 28.6 o
22 Compressor cascade performance From Figure 3.16, with s/l =1 and α* 2 = 28.6 o ε = α* 1 - α* 2 = 21 o α* 1 = 49 o i = α* 1 - α 1 = o
23 Compressor cascade performance Off design conditions To find the off design conditions, Howell generate the following curve. To find the off design conditions, you have to know the design conditions (*)
24 Compressor cascade performance
25 Turbine cascade performance Ainley (1948) Reaction turbine:- the fluid accelerates through the blade row and thus experiences a pressure drop during its passage impulse turbine:- no pressure change across an its blade row Notes form graph:- the reaction blades have a much wider range of low loss performance than the impulse blades the fluid outlet angle 2 remains relatively constant over the whole range of incidence for both types
26 Turbine cascade performance Ainley (1948)
27 Turbine cascade performance Ainley (1948)
28 Turbine cascade performance Ainley and Mathieson (1951) Total pressure loss correlations profile loss coefficient; Y p Ainley and Mathieson (1951) represent their results as graph of verses point at which where is the incidence at stalling point which is the
29 Turbine cascade performance Ainley and Mathieson (1951)
30 Turbine cascade performance Ainley and Mathieson (1951)
31 Turbine cascade performance Ainley and Mathieson (1951)
32 Turbine cascade performance For other types of blading intermediate between nozzle blades and impulse blades Secondary loss coefficient; Y s for blades of low aspect ratio, Dunham and Came (1970):- λ is a factor Z loading coefficient
33 Turbine cascade performance Tip clearance coefficient; Y k k : the size and nature of the clearance gap Flow outlet angle from a turbine cascade
34 Zweifel (1945) Turbine cascade performance Zweifel found from a number of experiments on turbine cascades that for minimum losses the value of Ψ T was approximately 0.8. Thus, for specified inlet and outlet angles the optimum space chord ratio can be estimated
Theory of turbo machinery. Chapter 3
Theory of turbo machinery Chapter 3 D cascades Let us first understand the facts and then we may seek the causes. (Aristotle) D cascades High hub-tip ratio (of radii) negligible radial velocities D cascades
More informationTheory of turbo machinery / Turbomaskinernas teori. Chapter 3
Theory of turbo achinery / Turboaskinernas teori Chapter 3 D cascades Let us first understand the facts and then we ay seek the causes. (Aristotle) D cascades High hub-tip ratio (of radii) negligible radial
More informationNumerical Investigation of Secondary Flow In An Axial Flow Compressor Cascade
Numerical Investigation of Secondary Flow In An Axial Flow Compressor Cascade 1 T. Suthakar, 2 Akash Dhurandhar 1 Associate Professor, 2 M.Tech. Scholar, Department of Mechanical Engineering National Institute
More informationContents. 1 Introduction to Gas-Turbine Engines Overview of Turbomachinery Nomenclature...9
Preface page xv 1 Introduction to Gas-Turbine Engines...1 Definition 1 Advantages of Gas-Turbine Engines 1 Applications of Gas-Turbine Engines 3 The Gas Generator 3 Air Intake and Inlet Flow Passage 3
More informationAxial Flow Compressors and Fans
5 Axial Flow Compressors and Fans 5.1 INTRODUCTION As mentioned in Chapter 4, the maximum pressure ratio achieved in centrifugal compressors is about 4:1 for simple machines (unless multi-staging is used)
More informationIn this lecture... Radial flow turbines Types of radial flow turbines Thermodynamics and aerodynamics Losses in radial flow turbines
Lect- 35 1 In this lecture... Radial flow turbines Types of radial flow turbines Thermodynamics and aerodynamics Losses in radial flow turbines Radial turbines Lect-35 Development of radial flow turbines
More informationTwo Dimensional Design of Axial Compressor An Enhanced Version of LUAX-C
Two Dimensional Design of Axial Compressor An Enhanced Version of LUAX-C Daniele Perrotti Thesis for the Degree of Master of Science Division of Thermal Power Engineering Department of Energy Sciences
More informationRestriction/ Classification Cancelled
Restriction/ Classification Cancelled NACA RM E55KOla SYMBOLS............................... 3 PRELIMINARY CONSIDERATIONS..................... 5 Description of Cascade...................... 5 Performance
More informationPerformance of an Axial Cascade
Open Journal of Fluid Dynamics, 213, 3, 191-197 http://dx.doi.org/1.4236/ojfd.213.3324 Published Online September 213 (http://www.scirp.org/journal/ojfd) Performance of an Axial Cascade Basharat Salim
More informationIntroduction to Turbomachinery
1. Coordinate System Introduction to Turbomachinery Since there are stationary and rotating blades in turbomachines, they tend to form a cylindrical form, represented in three directions; 1. Axial 2. Radial
More informationNumerical Investigation of Fluid Flows over a Rotor-Stator(Stage) in an Axial Flow Compressor Stage
Numerical Investigation of Fluid Flows over a Rotor-Stator(Stage) in an Axial Flow Compressor Stage Mr Vamsi Krishna Chowduru, Mr A Sai Kumar, Dr Madhu, Mr T Mahendar M.Tech (Thermal Engineering), MLR
More informationReynolds number effects on the aerodynamics of compact axial compressors
Paper ID: ETC27-227 Proceedings of 2th European Conference on Turbomachinery Fluid dynamics & Thermodynamics ETC2, April 3-7, 27; Stockholm, Sweden Reynolds number effects on the aerodynamics of compact
More informationCFD approach for design optimization and validation for axial flow hydraulic turbine
Indian Journal of Engineering & Materials Sciences Vol. 16, August 009, pp. 9-36 CFD approach for design optimization and validation for axial flow hydraulic turbine Vishnu Prasad, V K Gahlot* & P Krishnamachar
More informationExplicit algebraic Reynolds stress models for internal flows
5. Double Circular Arc (DCA) cascade blade flow, problem statement The second test case deals with a DCA compressor cascade, which is considered a severe challenge for the CFD codes, due to the presence
More informationLect-36. In this lecture... Tutorial on radial flow turbines. Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect- 36 1 In this lecture... Lect-36 Tutorial on radial flow turbines 2 Problem # 1 Lect-36 The rotor of an IFR turbine, which is designed to operate at the nominal condition, is 23.76 cm in diameter
More informationStator Blade Motor Motor Housing
The internal workings of a Ducted Fan The rotor velocity vectors and blade angles After looking at EDFs from a pure axial change of momentum position we must now address the question how the fan is shaped
More informationEffects of surface roughness on evolutions of loss and deviation in a linear compressor cascade
Journal of Mechanical Science and Technology 31 (11) (2017) 5329~5335 www.springerlink.com/content/1738-494x(print)/1976-3824(online) DOI 10.1007/s12206-017-1027-y Effects of surface roughness on evolutions
More informationPERFORMANCE ANALYSIS OF A TURBINE STAGE HAVING COOLED NOZZLE BLADES WITH TRAILING EDGE EJECTION
THE AMERCAN SOCETY OF MECHANCAL ENGNEERS 35 E. 7th St., New York. N.Y. 10077 96-TA-12 The Society shall not be responsible for statements or opinions advanced in papers or discussion at meetings of the
More informationNumerical Analysis of Partial Admission in Axial Turbines. Narmin Baagherzadeh Hushmandi
Numerical Analysis of Partial Admission in Axial Turbines Narmin Baagherzadeh Hushmandi Doctoral Thesis 2010 II Doctoral Thesis Report / Narmin B. Hushmandi 2009 ABSTRACT Numerical analysis of partial
More informationDepartment of Energy Sciences, LTH
Department of Energy Sciences, LTH MMV11 Fluid Mechanics LABORATION 1 Flow Around Bodies OBJECTIVES (1) To understand how body shape and surface finish influence the flow-related forces () To understand
More informationPerformance Investigation of High Pressure Ratio Centrifugal Compressor using CFD
International Journal of Ignited Minds (IJIMIINDS) Performance Investigation of High Pressure Ratio Centrifugal Compressor using CFD Manjunath DC a, Rajesh b, Dr.V.M.Kulkarni c a PG student, Department
More informationActive Control of Separated Cascade Flow
Chapter 5 Active Control of Separated Cascade Flow In this chapter, the possibility of active control using a synthetic jet applied to an unconventional axial stator-rotor arrangement is investigated.
More informationEffects of the Leakage Flow Tangential Velocity in Shrouded Axial Compressor Cascades *
TSINGHUA SCIENCE AND TECHNOLOGY ISSNll1007-0214ll21/21llpp105-110 Volume 14, Number S2, December 2009 Effects of the Leakage Flow Tangential Velocity in Shrouded Axial Compressor Cascades * KIM Jinwook
More informationContents. 2 Basic Components Aerofoils Force Generation Performance Parameters xvii
Contents 1 Working Principles... 1 1.1 Definition of a Turbomachine... 1 1.2 Examples of Axial Turbomachines... 2 1.2.1 Axial Hydraulic Turbine... 2 1.2.2 Axial Pump... 4 1.3 Mean Line Analysis... 5 1.4
More informationIMPLEMENTATION OF A SPANWISE MIXING MODEL FOR THROUGHFLOW CALCULATIONS IN AXIAL-FLOW COMPRESSORS
UNIVERSITÀ DEGLI STUDI DI PADOVA Dipartimento di Ingegneria Industriale DII Corso di Laurea Magistrale in Ingegneria Aerospaziale IMPLEMENTATION OF A SPANWISE MIXING MODEL FOR THROUGHFLOW CALCULATIONS
More informationContents. Preface... xvii
Contents Preface... xvii CHAPTER 1 Idealized Flow Machines...1 1.1 Conservation Equations... 1 1.1.1 Conservation of mass... 2 1.1.2 Conservation of momentum... 3 1.1.3 Conservation of energy... 3 1.2
More informationGPPS NUMERICAL PREDICTION OF UNSTEADY ENDWALL FLOW AND HEAT TRANSFER WITH ONCOMING WAKE
Proceedings of Shanghai 17 Global Power and Propulsion Forum 3 th October 1 st November, 17 http://www.gpps.global GPPS-17-133 NUMERICAL PREDICTION OF UNSTEADY ENDWALL FLOW AND HEAT TRANSFER WITH ONCOMING
More informationIn this lecture... Centrifugal compressors Thermodynamics of centrifugal compressors Components of a centrifugal compressor
Lect- 3 In this lecture... Centrifugal compressors Thermodynamics of centrifugal compressors Components of a centrifugal compressor Centrifugal compressors Centrifugal compressors were used in the first
More informationPrinciples of Turbomachinery
Principles of Turbomachinery To J. M. T. Principles of Turbomachinery R. K. Turton Lecturer in Mechanical Engineering Loughborough University of Technology London New York E. & F. N. Spon ISBN 978-94-010-9691-1
More informationP. V. Ramakrishna and M. Govardhan. 1. Introduction
International Journal of Rotating Machinery Volume 9, Article ID 78745, pages doi:.55/9/78745 Research Article Study of Sweep and Induced Dihedral Effects in Subsonic Axial Flow Compressor Passages Part
More informationExperimental Study of the Flow in a Linear Cascade of Axial Compressor Blades
Experimental Study of the Flow in a Linear Cascade of Axial Compressor Blades Miguel Toledo-Velázquez, Guilibaldo Tolentino-Eslava, Miguel Leonardo Cervera-Morales, Juan Abugaber-Francis, Luis René Rangel-López
More informationTHE AMERICAN SOCIETY OF MECHANICAL ENGINEERS Three Perk Avenue, New YoriL N.Y Institute of Turbomachinery
THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS Three Perk Avenue, New YoriL N.Y. 100164990 99-GT-103 The Society shall not be responsible for statements or opinions advanced in papers or discussion at meetings
More informationLect 22. Radial Flow Turbines. Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lecture Lect Radial Flow Turbines Lect Radial inflow turbines, which look similar to centrifugal compressor, are considered suitable for application in small aircraft engines. In many applications a radial
More informationChapter Two. Basic Thermodynamics, Fluid Mechanics: Definitions of Efficiency. Laith Batarseh
Chapter Two Basic Thermodynamics, Fluid Mechanics: Definitions of Efficiency Laith Batarseh The equation of continuity Most analyses in this book are limited to one-dimensional steady flows where the velocity
More informationNUMERICAL SIMULATION OF STATIC INFLOW DISTORTION ON AN AXIAL FLOW FAN
Int. J. Mech. Eng. & Rob. Res. 2014 Arun Raj S and Pal Pandian P, 2014 Research Paper ISSN 2278 0149 www.ijmerr.com Vol. 3, No. 2, April 2014 2014 IJMERR. All Rights Reserved NUMERICAL SIMULATION OF STATIC
More informationAxial length impact on high-speed centrifugal compressor flow
Fluid Structure Interaction VII 263 Axial length impact on high-speed centrifugal compressor flow P. Le Sausse 1,2,P.Fabrie 1 & D. Arnou 2 1 Université de Bordeaux, IPB, UMR5251, ENSEIRB-MATMECA, Talence,
More informationIMPACT OF FLOW QUALITY IN TRANSONIC CASCADE WIND TUNNELS: MEASUREMENTS IN AN HP TURBINE CASCADE
1 ICAS 2002 CONGRESS IMPACT OF FLOW QUALITY IN TRANSONIC CASCADE WIND TUNNELS: MEASUREMENTS IN AN HP TURBINE CASCADE D. Corriveau and S.A. Sjolander Dept. of Mechanical & Aerospace Engineering Carleton
More informationIntroduction to Fluid Machines and Compressible Flow Prof. S.K Som Department of Mechanical Engineering Indian Institute of Technology, Kharagpur
Introduction to Fluid Machines and Compressible Flow Prof. S.K Som Department of Mechanical Engineering Indian Institute of Technology, Kharagpur Lecture No. # 24 Axial Flow Compressor Part I Good morning
More informationLOSSES THROUGH CASCADE TESTING
ESTIMATION OF TURBOMACHINERY FLOW LOSSES THROUGH CASCADE TESTING A lecture by KMM SWAMY & R SENTHIL KUMARAN Scientists t Propulsion Division, i i National Aerospace Laboratories for two day seminar on
More informationTurbomachinery Flow Physics and Dynamic Performance
Turbomachinery Flow Physics and Dynamic Performance Bearbeitet von Meinhard T Schobeiri 1. Auflage 2004. Buch. XXI, 522 S. Hardcover ISBN 978 3 540 22368 9 Format (B x L): 15,5 x 23,5 cm Gewicht: 2070
More informationApplication of Analytical and Numerical Methods for the Design of Transonic Axial Compressor Stages
Application of Analytical and Numerical Methods for the Design of Transonic Axial Compressor tages rof. Dr.-Ing. Martin Böhle Mechanical Engineering University of Wuppertal Gaußstraße 0, 4097 Wuppertal
More informationLARGE EDDY SIMULATION OF FLOW OVER NOZZLE GUIDE VANE OF A TRANSONIC HIGH PRESSURE TURBINE
20 th Annual CFD Symposium, August 09-10, 2018, Bangalore LARGE EDDY SIMULATION OF FLOW OVER NOZZLE GUIDE VANE OF A TRANSONIC HIGH PRESSURE TURBINE Bharathan R D, Manigandan P, Vishal Tandon, Sharad Kapil,
More informationEFFECT OF REYNOLDS NUMBER ON SEPARATION BUBBLES ON CONTROLLED-DIFFUSION COMPRESSOR BLADES IN CASCADE
EFFECT OF REYNOLDS NUMBER ON SEPARATION BUBBLES ON CONTROLLED-DIFFUSION COMPRESSOR BLADES IN CASCADE Garth V. Hobson * Denis J. Hansen **, David G. Schnorenberg ** and Darren V. Grove ** Department of
More informationRadial Turbine with Pitch-controlled Guide Vanes for Wave Energy Conversion
Radial Turbine with Pitch-controlled Guide Vanes for Wave Energy Conversion M. Takao 1, M. Suzuki, T. Setoguchi 3, B. Pereiras and F. Castro 1 Department of Mechanical Engineering, Matsue College of Technology,
More informationTheory and Applica0on of Gas Turbine Systems
Theory and Applica0on of Gas Turbine Systems Part IV: Axial and Radial Flow Turbines Munich Summer School at University of Applied Sciences Prof. Kim A. Shollenberger Introduc0on to Turbines Two basic
More information3. Write a detailed note on the following thrust vector control methods:
Code No: R05322103 Set No. 1 1. Starting from the first principles and with the help of neatly drawn velocity triangles obtain the following relationship: Ψ = 2 Φ (tan β 2 + tan β 3 ) where Ψ is the blade
More informationGiven a stream function for a cylinder in a uniform flow with circulation: a) Sketch the flow pattern in terms of streamlines.
Question Given a stream function for a cylinder in a uniform flow with circulation: R Γ r ψ = U r sinθ + ln r π R a) Sketch the flow pattern in terms of streamlines. b) Derive an expression for the angular
More informationInternational Journal of Research in Advent Technology Available Online at:
A COMPUTER PROGRAMMED DESIGN OPTIMISATION AND ANALYSIS OF COMPRESSOR IMPELLER G. Naga Malleshwar Rao 1, Dr. S.L.V. Prasad 2, Dr. S. Sudhakarbabu 3 1, 2 Professor of Mechanical Engineering, Shri Shirdi
More information1. Fluid Dynamics Around Airfoils
1. Fluid Dynamics Around Airfoils Two-dimensional flow around a streamlined shape Foces on an airfoil Distribution of pressue coefficient over an airfoil The variation of the lift coefficient with the
More informationCHAPTER 4 OPTIMIZATION OF COEFFICIENT OF LIFT, DRAG AND POWER - AN ITERATIVE APPROACH
82 CHAPTER 4 OPTIMIZATION OF COEFFICIENT OF LIFT, DRAG AND POWER - AN ITERATIVE APPROACH The coefficient of lift, drag and power for wind turbine rotor is optimized using an iterative approach. The coefficient
More informationANALYSIS OF INTERFERENCE FACTORS OF AIR TURBINE CASCADES
Engineering Applications of Computational Fluid Mechanics Vol. 7, No. 4, pp. 496 506 (2013) ANALYSIS OF INTERFERENCE FACTORS OF AIR TURBINE CASCADES Andrei Gareev, Buyung Kosasih * and Paul Cooper School
More informationCOMPUTER AIDED DESIGN OF RADIAL TIPPED CENTRIFUGAL BLOWERS AND FANS
4 th International Conference on Mechanical Engineering, December 26-28, 21, Dhaka, Bangladesh/pp. IV 55-6 COMPUTER AIDED DESIGN OF RADIAL TIPPED CENTRIFUGAL BLOWERS AND FANS Nitin N. Vibhakar* and S.
More informationPlease welcome for any correction or misprint in the entire manuscript and your valuable suggestions kindly mail us
Problems of Practices Of Fluid Mechanics Compressible Fluid Flow Prepared By Brij Bhooshan Asst. Professor B. S. A. College of Engg. And Technology Mathura, Uttar Pradesh, (India) Supported By: Purvi Bhooshan
More informationStudy on the Performance of a Sirocco Fan (Flow Around the Runner Blade)
Rotating Machinery, 10(5): 415 424, 2004 Copyright c Taylor & Francis Inc. ISSN: 1023-621X print / 1542-3034 online DOI: 10.1080/10236210490474629 Study on the Performance of a Sirocco Fan (Flow Around
More informationMODELLING PARTICLE DEPOSITION ON GAS TURBINE BLADE SURFACES
MODELLING PARTICLE DEPOSITION ON GAS TURBINE BLADE SURFACES MS. Hesham El-Batsh Institute of Thermal Turbomachines and Power Plants Vienna University of Technology Getreidemarkt 9/313, A-1060 Wien Tel:
More informationThe Measurement and Prediction of the Tip Clearance Flow in Linear Turbine Cascades
THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS 345 E. 47 St., New York, N.Y. 117 92-GT-214 The Society shall not be responsible for statements or opinions advanced in papers or in discussion at meetings
More informationA metastable wet steam turbine stage model
Nuclear Engineering and Design 16 (00) 113 119 www.elsevier.com/locate/nucengdes A metastable wet steam turbine stage Wageeh Sidrak Bassel *, Arivaldo Vicente Gomes Instituto de Pesquisas Energeticas e
More informationLecture 7 Boundary Layer
SPC 307 Introduction to Aerodynamics Lecture 7 Boundary Layer April 9, 2017 Sep. 18, 2016 1 Character of the steady, viscous flow past a flat plate parallel to the upstream velocity Inertia force = ma
More informationNUMERICAL INVESTIGATION OF VERTICAL AXIS WIND TURBINE WITH TWIST ANGLE IN BLADES
Eleventh International Conference on CFD in the Minerals and Process Industries CSIRO, Melbourne, Australia 7-9 December 05 NUMERICAL INVESTIGATION OF VERTICAL AXIS WIND TURBINE WITH TWIST ANGLE IN BLADES
More informationKeywords - Gas Turbine, Exhaust Diffuser, Annular Diffuser, CFD, Numerical Simulations.
Numerical Investigations of PGT10 Gas Turbine Exhaust Diffuser Using Hexahedral Dominant Grid Vaddin Chetan, D V Satish, Dr. Prakash S Kulkarni Department of Mechanical Engineering, VVCE, Mysore, Department
More information(Refer Slide Time: 4:41)
Fluid Machines. Professor Sankar Kumar Som. Department Of Mechanical Engineering. Indian Institute Of Technology Kharagpur. Lecture-30. Basic Principle and Energy Transfer in Centrifugal Compressor Part
More informationCOMPUTATIONAL SIMULATION OF THE FLOW PAST AN AIRFOIL FOR AN UNMANNED AERIAL VEHICLE
COMPUTATIONAL SIMULATION OF THE FLOW PAST AN AIRFOIL FOR AN UNMANNED AERIAL VEHICLE L. Velázquez-Araque 1 and J. Nožička 2 1 Division of Thermal fluids, Department of Mechanical Engineering, National University
More informationMECA-H-402: Turbomachinery course Axial compressors
MECA-H-40: Turbomachinery course Axial compressors Pr. Patrick Hendrick Aero-Thermo-Mecanics Year 013-014 Contents List of figures iii 1 Axial compressors 1 1.1 Introduction...............................
More informationCHAPTER 3 ANALYSIS OF NACA 4 SERIES AIRFOILS
54 CHAPTER 3 ANALYSIS OF NACA 4 SERIES AIRFOILS The baseline characteristics and analysis of NACA 4 series airfoils are presented in this chapter in detail. The correlations for coefficient of lift and
More informationLarge-eddy simulations for wind turbine blade: rotational augmentation and dynamic stall
Large-eddy simulations for wind turbine blade: rotational augmentation and dynamic stall Y. Kim, I.P. Castro, and Z.T. Xie Introduction Wind turbines operate in the atmospheric boundary layer and their
More informationPEMP RMD510. M.S. Ramaiah School of Advanced Studies, Bengaluru
Design of Axial Flow Compressor- Session delivered by: Prof. Q. H. Nagpurwala Session Objectives To learn design procedure for axial compressor stages To calculate flow properties across the blade rows
More informationImproved Model for Meanline Analysis of Centrifugal Compressors with a Large Tip Clearance
Improved Model for Meanline Analysis of Centrifugal Compressors with a Large Tip Clearance Andrey Sherbina 1, Ivan Klimov 2 and Leonid Moroz 3 SoftInWay Inc., 1500 District Avenue, Burlington, MA, 01803,
More informationANALYTICAL MODELING OF HELIUM TURBOMACHINERY USING FORTRAN 77 PURUSHOTHAM BALAJI. Presented to the Faculty of the Graduate School of
ANALYTICAL MODELING OF HELIUM TURBOMACHINERY USING FORTRAN 77 by PURUSHOTHAM BALAJI Presented to the Faculty of the Graduate School of The University of Texas at Arlington in Partial Fulfillment of the
More informationFinite Element Method for Turbomachinery Flows
SOCRATES Teaching Staff Mobility Program 2000-2001 DMA-URLS Finite Element Method for Turbomachinery Flows Numerical studies on axial flow fan rotor aerodynamics Alessandro Corsini Dipartimento di Meccanica
More informationGiven the water behaves as shown above, which direction will the cylinder rotate?
water stream fixed but free to rotate Given the water behaves as shown above, which direction will the cylinder rotate? ) Clockwise 2) Counter-clockwise 3) Not enough information F y U 0 U F x V=0 V=0
More informationWind Turbine Blade Analysis using the Blade Element Momentum Method. Version 1.0
using the Blade Element Momentum Method. Version 1.0 Grant Ingram December 13, 2005 Copyright c) 2005 Grant Ingram, All Rights Reserved. 1 Contents 1 Introduction 5 2 Blade Element Momentum Theory 5 3
More informationCOMPUTATIONAL METHOD
Multi Objective Design Optimization of Rocket Engine Turbopump Turbine Naoki Tani, Akira Oyama and Nobuhiro Yamanishi tani.naoki@jaxa.jp Japan Aerospace Exploration Agency JAXA is now planning to develop
More informationThe Effect of Diameter Ratio on the Performance of a Low, Stagger Axial-Compressor Stage
... i96o.~ ~ ~ ~,~"~; -,, " R. & M. No. 3151 (15,023) A.R.C. Technical Report MINISTRY OF AVIATION AERONAUTICAL RESEARCH COUNCIL REPORTS AND MEMORANDA The Effect of Diameter Ratio on the Performance of
More informationSupersonic Turbine Design and Performance
72-GT-63 $3.00 PER COPY $1.00 TO ASME MEMBERS The Society shall not be responsible for statements or opinions advanced in papers or in discussion at meetings of the Society or of its Divisions or Sections,
More informationGTINDIA CFD ANALYSIS TO UNDERSTAND THE FLOW BEHAVIOUR OF A SINGLE STAGE TRANSONIC AXIAL FLOW COMPRESSOR. 1 Copyright 2013 by ASME
Proceedings of ASME GTINDIA 203 ASME 203 GAS TURBINE INDIA CONFERENCE DECEMBER 5-6, 203, BANGALORE, KARNATAKA, INDIA GTINDIA203-3592 CFD ANALYSIS TO UNDERSTAND THE FLOW BEHAVIOUR OF A SINGLE STAGE TRANSONIC
More informationBlade Element Momentum Theory
Blade Element Theory has a number of assumptions. The biggest (and worst) assumption is that the inflow is uniform. In reality, the inflow is non-uniform. It may be shown that uniform inflow yields the
More informationSteam and Gas Power Systems Prof. Ravi Kumar Department of Mechanical industrial engineering Indian Institute of Technology Roorkee
Steam and Gas Power Systems Prof. Ravi Kumar Department of Mechanical industrial engineering Indian Institute of Technology Roorkee Module No # 06 Lecture No # 26 Impulse Reaction Steam Turbines Hello
More informationA Numerical study of effect of Return Channel Vanes Shroud Wall Divergence Angle on the Cross-over System Performance in Centrifugal Compressors
RESEARCH ARTICLE OPEN ACCESS A Numerical study of effect of Return Channel Vanes Shroud Wall Divergence Angle on the Cross-over System Performance in Centrifugal Compressors * K.Srinivasa Reddy *, M Sai
More informationDesign and simulation of flow through subsonic axial compressor
Design and simulation of flow through subsonic axial compressor Mutahir Ahmed 1, Saeed Badshah 2, Rafi Ullah Khan 2, Muhammad sajjad 2, Sakhi Jan 2 1 NESCOM, Islamabad Pakistan 2 Department of Mechanical
More informationStudy of Flow Patterns in Radial and Back Swept Turbine Rotor under Design and Off-Design Conditions
Journal of Applied Fluid Mechanics, Vol. 9, No. 4, pp. 1791-1798, 2016. Available online at www.jafmonline.net, ISSN 1735-3572, EISSN 1735-3645. DOI: 10.18869/acadpub.jafm.68.235.24206 Study of Flow Patterns
More informationEXPERIMENT No.1 FLOW MEASUREMENT BY ORIFICEMETER
EXPERIMENT No.1 FLOW MEASUREMENT BY ORIFICEMETER 1.1 AIM: To determine the co-efficient of discharge of the orifice meter 1.2 EQUIPMENTS REQUIRED: Orifice meter test rig, Stopwatch 1.3 PREPARATION 1.3.1
More informationNumerical Analysis of Active Cascade Flutter Control with Smart Structure
Proceedings of the International Gas Turbine Congress Tokyo November -7, IGTCTokyo TS-55 Numerical Analysis of Active Cascade Flutter Control with Smart Structure Junichi Kazawa and Toshinori Watanabe
More informationA Numerical Study of Circulation Control on a Flapless UAV
Ninth International Conference on Computational Fluid Dynamics (ICCFD9), Istanbul, Turkey, July 11-15, 2016 ICCFD9-xxxx A Numerical Study of Circulation Control on a Flapless UAV Huaixun Ren 1, Weimin
More informationINFLUENCE OF ROTATING STALL AND SURGE IN THE DESIGN OF A SMALL GAS TURBINE ENGINE WITH AXIAL FLOW COMPRESSOR
Proceedings of the th Brazilian Congress of Thermal Sciences and Engineering ENCIT 6 Braz. Soc. of Mechanical Sciences and Engineering ABCM, Curitiba, Brazil, Dec. 5-8, 6 Paper CIT6-96 INFLUENCE OF ROTATING
More informationProf. Dr.-Ing. F.-K. Benra. ISE Bachelor Course
University Duisburg-Essen Campus Duisburg Faculty of Engineering Science Examination: Fluid Machines Examiner: Prof. Dr.-Ing. F.-K. Benra Date of examination: 07.08.2006 Handling time: 120 Minutes ISE
More informationAerodynamics. Basic Aerodynamics. Continuity equation (mass conserved) Some thermodynamics. Energy equation (energy conserved)
Flow with no friction (inviscid) Aerodynamics Basic Aerodynamics Continuity equation (mass conserved) Flow with friction (viscous) Momentum equation (F = ma) 1. Euler s equation 2. Bernoulli s equation
More informationInfluence of Chord Lengths of Splitter Blades on Performance of Small Axial Flow Fan
Send Orders for Reprints to reprints@benthamscience.ae The Open Mechanical Engineering Journal, 2015, 9, 361-370 361 Open Access Influence of Chord Lengths of Splitter Blades on Performance of Small Axial
More informationLarge-eddy simulation of a compressor rotor
Center for Turbulence Research Proceedings of the Summer Program 214 467 Large-eddy simulation of a compressor rotor By J. Joo, G. Medic, D. A. Philips AND S. T. Bose Wall-modeled large-eddy simulation
More informationElliptic Trailing Edge for a High Subsonic Turbine Cascade
Elliptic Trailing Edge for a High Subsonic Turbine Cascade Mahmoud M. El-Gendi 1, Mohammed K. Ibrahim 2, Koichi Mori 3, and Yoshiaki Nakamura 4 1 Graduate School of Engineering, Nagoya University, Nagoya
More informationSPC Aerodynamics Course Assignment Due Date Monday 28 May 2018 at 11:30
SPC 307 - Aerodynamics Course Assignment Due Date Monday 28 May 2018 at 11:30 1. The maximum velocity at which an aircraft can cruise occurs when the thrust available with the engines operating with the
More informationFlight Vehicle Terminology
Flight Vehicle Terminology 1.0 Axes Systems There are 3 axes systems which can be used in Aeronautics, Aerodynamics & Flight Mechanics: Ground Axes G(x 0, y 0, z 0 ) Body Axes G(x, y, z) Aerodynamic Axes
More informationThe Performance of Supersonic Turbine Nozzles
- ':~,~1 ~ 4"v:~.~, '' ': "~: ;! R. & M. No. 3273 MNSTRY OF AVATON AERONAUTCAL RESEARCH COUNCL REPORTS AND MEMORANDA The Performance of Supersonic Turbine Nozzles By B. S. STRATFORD and G. E. SANSOME LONDON:
More informationFlow analysis in centrifugal compressor vaneless diffusers
348 Journal of Scientific & Industrial Research J SCI IND RES VOL 67 MAY 2008 Vol. 67, May 2008, pp. 348-354 Flow analysis in centrifugal compressor vaneless diffusers Ozturk Tatar, Adnan Ozturk and Ali
More informationResearch Article Quasi-Steady Analytical Model Benchmark of an Impulse Turbine for Wave Energy Extraction
International Journal of Rotating Machinery Volume 008, Article ID 56079, pages doi:0.55/008/56079 Research Article Quasi-Steady Analytical Model Benchmark of an Impulse Turbine for Wave Energy Extraction
More informationAE 2020: Low Speed Aerodynamics. I. Introductory Remarks Read chapter 1 of Fundamentals of Aerodynamics by John D. Anderson
AE 2020: Low Speed Aerodynamics I. Introductory Remarks Read chapter 1 of Fundamentals of Aerodynamics by John D. Anderson Text Book Anderson, Fundamentals of Aerodynamics, 4th Edition, McGraw-Hill, Inc.
More informationCOURSE NUMBER: ME 321 Fluid Mechanics I 3 credit hour. Basic Equations in fluid Dynamics
COURSE NUMBER: ME 321 Fluid Mechanics I 3 credit hour Basic Equations in fluid Dynamics Course teacher Dr. M. Mahbubur Razzaque Professor Department of Mechanical Engineering BUET 1 Description of Fluid
More informationSMITH DIAGRAM FOR LOW REYNOLDS NUMBER AXIAL FAN ROTORS
Paper ID: ETC2017-069 Proceedings of 12th European Conference on Turbomachinery Fluid dynamics & Thermodynamics ETC12, April 3-7, 2017; Stockholm, Sweden SMITH DIAGRAM FOR LOW REYNOLDS NUMBER AXIAL FAN
More informationNumerical Study of Pressure and Velocity Distribution Analysis of Centrifugal Pump
International Journal of Thermal Technologies, Vol.1, No.1 (Dec. 2011) Research Article Numerical Study of Pressure and Velocity Distribution Analysis of Centrifugal Pump Munish Gupta 1, Satish Kumar 2,
More informationEngineering Fluid Mechanics
Engineering Fluid Mechanics Eighth Edition Clayton T. Crowe WASHINGTON STATE UNIVERSITY, PULLMAN Donald F. Elger UNIVERSITY OF IDAHO, MOSCOW John A. Roberson WASHINGTON STATE UNIVERSITY, PULLMAN WILEY
More information