Design of Radial Turbines & Turbochargers
|
|
- Godwin York
- 5 years ago
- Views:
Transcription
1 RMD50 Design of Radial Turbines & Turbochargers Session delivered by: Prof. Q. H. Nagpurwala M S Ramaiah School of Advanced Studies, Bengaluru
2 Session Objective RMD50 To discuss the design of radial turbines using a procedure based on optimum specific speed To understand the basic construction and working of turbochargers To discuss the design of radial compressor and radial turbine modules of a typical turbocharger M S Ramaiah School of Advanced Studies, Bengaluru
3 RMD50 Design of Radial Turbine (Based on Specific Speed) M S Ramaiah School of Advanced Studies, Bengaluru 3
4 RMD50 Radial Turbine Layout and Expansion Process Nozzle blades At rotor inlet At rotor outlet Expansion process in a radial turbine M S Ramaiah School of Advanced Studies, Bengaluru 4
5 Design Guidelines RMD50 From Euler turbine equation, specific work is given by: A significant contribution comes from the first term. For an axial flow turbine, where U = U, no contribution to the specific work is obtained from this term. A positive contribution to the specific work is obtained from the second term when w 3 > w. In fact, accelerating the relative velocity through the rotor is a most useful aim of the designer as this is conducive to achieving a low loss flow. The third term indicates that the absolute velocity at rotor inlet should be larger than at rotor outlet so as to increase the work input to the rotor. M S Ramaiah School of Advanced Studies, Bengaluru 5
6 Design Guidelines RMD50 The nominal design is defined by relative flow with zero incidence at rotor inlet, i.e. W = r, and axial absolute flow at rotor exit, i.e. 3 = x3 Thus, with w3 = 0 and w = U, the specific work for the nominal design is Spouting Velocity: The term spouting velocity, 0 (originating from hydraulic turbine practice) is defined as that velocity which has an associated kinetic energy equal to the isentropic enthalpy drop from turbine inlet stagnation pressure p 0 to the final exhaust pressure. When no diffuser is used or With complete recovery of the exhaust kinetic energy, and with w = U, At the best efficiency point, generally, 0.68 < U / 0 < 0.7. M S Ramaiah School of Advanced Studies, Bengaluru 6
7 Design Guidelines RMD50 The blades are aligned along the radii for much of their length. Absolute flow angle at rotor inlet = Nozzle outlet angle = ~ 70º. Absolute flow angle at exducer exit = 0º. Inlet relative velocity should be aligned to the blade direction at inlet, which means that it should be radial. However, this may lead to high aerodynamic loading at the tip as the blade tips are open, such high pressure loading can not be maintained Max. efficiency in radial inflow turbines is achieved when inlet flow angle is modified by the concept of slip or deviation as applied to radial compressors. The recommended ddslip correlation lti is that thtgiven by Wiesner w u,, ac cos 0.7 u,, tl Z Z = number of blades (incl. splitter blades) = blade angle w.r.t radial direction M S Ramaiah School of Advanced Studies, Bengaluru 7
8 Variation of Slip Factor with Z RMD50 The slip factor for radial bladed rotor varies with the number of blades: Number of radial blades Slip factor on rotor periphery p u, /u M S Ramaiah School of Advanced Studies, Bengaluru 8
9 Design Data RMD50 Inlet temperature : 00 K Inlet pressure : Pa Rotor-outlet stagnation pressure : Pa Hot-gas inlet mass flow : 0.5 kg/s Fuel/Air ratio : 0.0 Number of rotor blades : 3 (radial) Nozzle outflow angle : 70 to radial direction To find: Rotor diameter Blade axial width at inlet Rotational speed M S Ramaiah School of Advanced Studies, Bengaluru 9
10 Inlet Velocity Triangle RMD50 act c r r, W u, u M S Ramaiah School of Advanced Studies, Bengaluru 0
11 Inlet Flow Parameters RMD50 Guess Stagnation-to-Stagnation polytropic efficiency = 0.9 For 3 blades w = = Then, T T T c 0, 0, p p 0, 0, p Δh Δh 0 0 u, p ψ u ΔT K u r, 8. m/s W R p, c p J/kg K 85, 089 m/s m/s m/s c T 0, = K J/kg m/s c act r, u, M S Ramaiah School of Advanced Studies, Bengaluru u W
12 Optimum Specific Speed RMD50 Distribution of losses along envelope of maximum total-to-static efficiency (Rohlik 968) Typical performance of radial turbine (Rohlik 968) M S Ramaiah School of Advanced Studies, Bengaluru
13 Optimum Specific Speed ( contd.) RMD50 urves for specific speed for radial flow turbine indicate that the max. efficiency should reach at non-dimensional N s of 0.6. N u s,op 0. 6 ωr πn 60 πn 60 V in Δh 3 4 d Vin r, π d b r, g c Δh 0 ω N s ψ u r, π d b 3 4 ψ u πnd 60 π d d b d M S Ramaiah School of Advanced Studies, Bengaluru 3
14 Rotor Inlet Width to Diameter Ratio RMD50 tan b d b d N ψ u N s ψ s u ω d π r, 4π r, ψ u αc, r, N ψ tan α 4π b s c, Inserting appropriate design inputs, we get b /d = 0.07 Both hbb and d can be determined dby calculating l volume flow rate at rotor inlet RT g c 0, M S Ramaiah School of Advanced Studies, Bengaluru 4
15 RMD50 Rotor Inlet Mach Number Mach number can be determined from the following relation or the figure R M R RT g p p c R M M S Ramaiah School of Advanced Studies, Bengaluru 5
16 alculation of Density RMD50 ρ ρ st, 0, p R M p R The stagnation density at rotor inlet can be assumed equal to that at nozzle inlet for this preliminary design 3 RT ρ 0, p 0, 0, 0 ρ st, kg k m 0.87 kg M S Ramaiah School of Advanced Studies, Bengaluru 6 m 3
17 Rotational Speed RMD50 m d b u d r, ρst, π d b r, ρ st, π mm mm N πn d u πd rpm π d b d M S Ramaiah School of Advanced Studies, Bengaluru 7
18 Final Design RMD50 Having found the basic geometric parameters of the rotor (and inlet nozzle vanes), the blade profiles can be generated by using analytic equations using i commercial software, like BLADEGEN The final design has to be arrived at through iteration between structural integrity (considering aerodynamic and thermal loading) and aerodynamic performance. Finally, the mechanical design should be carried out, taking due care of the component manufacturing and assembly requirements. Inlet Nozzle vane Exit Exducer M S Ramaiah School of Advanced Studies, Bengaluru 8
19 RMD50 Design of Turbocharger (Based on Specific Speed) M S Ramaiah School of Advanced Studies, Bengaluru 9
20 Schematic of a Turbocharger RMD50 M S Ramaiah School of Advanced Studies, Bengaluru 0
21 Turbocharger omponents RMD50 M S Ramaiah School of Advanced Studies, Bengaluru
22 Working of Turbocharger RMD50 M S Ramaiah School of Advanced Studies, Bengaluru
23 Turbocharger Design Data RMD50 ompressor Turbine Mass flow rate, kg/s.0.04 Inlet stagnation temperature, K 300 (T 0 0, ) 800 (T 04 0,4 ) Inlet stagnation pressure, N/m *0 5 (P 0, ) Find Engine back pressure (P 0,4 ) Outlet static pressure, N/m * 0 5 (P st,3 ).* 0 5 (P st,7 ) Fluid ud Air ombustion o products 00% theoretical air p J/(kg K ) & ( p /R ) 00 (3.5) 7 (4084) Blade angle at periphery p 30 ( ) 0 ( 5 ) Specific speed, Ns d hb, / d sh, Polytropic oy opcefficiency cy 0.8 ( pts p,ts,-3 3 ) 0.8 ( pts4 p,ts,4-7 7 ) Flow angle at rotor exit, c (deg) 60 0 Flow angle at rotor inlet, c (deg) 0 70 Number of rotor blades, Z 7 3 Polytropic efficiency 0.96 ( p,tt,- ) 0.96 ( p,tt,5-6 ) M S Ramaiah School of Advanced Studies, Bengaluru 3
24 alculations Planes RMD50 M S Ramaiah School of Advanced Studies, Bengaluru 4
25 Wiesner s orrelation RMD50 This correlation, defining slip factor,, can be used to calculate the number of blades, Z, in the radial turbine as well as in the radial compressor. σ w u,,ac u,,tl Z cos β 0. 7 Z M S Ramaiah School of Advanced Studies, Bengaluru 5
26 RMD50 ompressor Design alculations M S Ramaiah School of Advanced Studies, Bengaluru 6
27 ompressor Velocity Triangles RMD50 u u,,tl u, r, W c =60 =30 Outlet Velocity Triangle u sh, xsh x,sh, W w,sh, sh, Inlet Velocity Triangle M S Ramaiah School of Advanced Studies, Bengaluru 7
28 Enthalpy Rise RMD50 T T p 0, 3 p0, 3 0, 0, 3 p p st, 3 0, R p when η p,c,ts η p,c,ts is used T 0, T 0, ΔT, K pc 00 J/kgK Therefore, and Δh 0, 3 87 J/kg 3 4 Δh g c, 3 M S Ramaiah School of Advanced Studies, Bengaluru 8
29 Inlet Volume Flow Rate RMD50 Guess inlet axial velocity First iteration: 0 m/s Second iteration: 7.3 m/s (all second iteration values are in parenthesis) g For ρ ρ 0 st c RT x p 0, R , M M p R p 0. 3 R From slide 5 M S Ramaiah School of Advanced Studies, Bengaluru 9
30 Rotational Speed RMD50 ρ p0, 66. kg/m RT , 0, ρ st, 04. m ρ V st, kg/m ( ) V V. N 3 m /s m /s, 60N s g c Δh π V V V rev/min M S Ramaiah School of Advanced Studies, Bengaluru 30
31 RMD50 ompressor Outlet Velocity Diagram From Wiesner s correlation (slide 5) u,ac u,tl For u u, u d cos σ w β tan β tan αc u u,,tl u, cos β Z r, W cos30,z 7 c =60 =30 g c Δh 0 ψ 60u / N σ 0. 5 w mm 0. 5 ψ m/s M S Ramaiah School of Advanced Studies, Bengaluru 3
32 Inlet Velocity Diagram RMD50 The procedure to select minimum i W sh, is as follows. hoose a valueof dsh,.alculate 3.alculate 4.alculate u A sh, a m Nπ / 60 d πd / RT 0, sh, /A a p 0, sh, m RT0 /gc M M 5. from the relation AP 0 R p calculate M p R 6. alculate pst, /p0, pst, x, Wsh, p R This procedure is given in tabular form in Slide 33, in which the second iteration values are given in brackets. The optimum value of d sh, is found to be 0 mm. M S Ramaiah School of Advanced Studies, Bengaluru 3
33 RMD50 alculation of Optimum Shroud Parameter d sh, (mm) u sh, (m/s) = d sh, (= 575. d sh, ) (57.) (99.64) (9.65) 3 A ( m ) d a sh, m RT , /A p0, M x, ρ st, /ρ (m/s ) W 0, A a. ρ st, u /ρ 0, sh, x, sh, (58.5) (30.9) (30.) M S Ramaiah School of Advanced Studies, Bengaluru 33
34 Impeller-Diffuser Interface RMD50 The minimum value of W sh, is found to be 30. m/s. Hence, the de Haller velocity ratio, W / W sh, = This should not lead to diffusion induced separation. Impeller-Outlet and diffuser-inlet width, b : ψu sin αc, T 0, M ρ st, ρ 0, K g c RT , m/s M S Ramaiah School of Advanced Studies, Bengaluru 34
35 Inducer Hub-Tip Ratio RMD50 Find the rotor-outlet tl t stagnation ti pressure using the rotor efficiency i Therefore, p p p ρ ρ 0, 0, 0, 0, st, r, T T 0, 0, R p kg/m cos 60 kg/m ηp,c,tt, N/m 3 3 πd ρ mm b m st, r, 37. m/s Inducer hub diameter can be determined from hub-tip ratio d hb, d hb, mm d sh, M S Ramaiah School of Advanced Studies, Bengaluru 35
36 Radial Diffuser Stability RMD50 for mean R e, T st, μ d μ 30K st, R e,. 440 b r 6 ρ st, Ns/m From the Stability limits in Jansen s curves b / r (r 3 / r ) mx (by interpolation) 80 percent of.0 is.6 d 3 =.6 x 9. = 350 mm M S Ramaiah School of Advanced Studies, Bengaluru 36
37 Radial Diffuser Stability ( contd.) RMD50 Stable operating range of vaneless diffusers (Jansen, 964) M S Ramaiah School of Advanced Studies, Bengaluru 37
38 RMD50 Turbine Design alculations M S Ramaiah School of Advanced Studies, Bengaluru 38
39 Turbine Design alculations RMD50 Turbine Rotor Diameter: The turbine has slightly increased mass flow, because of fuel addition, and must supply windage and dbearing power in addition to compressor power. 0. Δh0,e 877 J/kg 04. u u u, 5 u, 5,tl u, 5,tl 5 cos 0. 7 Z e u u, 5,ac 5 u 5 β 5 and β * m/s d5 ; Z e u 5 g c u u, 5 5 mm M S Ramaiah School of Advanced Studies, Bengaluru 39
40 Turbine Design alculations RMD50 Turbine Pressure Ratio: m e Δh 0,e. 0 m c Δh 0,c ΔT p p p ,e K 0,in 0,ex 0,ex T T 0,in 0,ex p st,ex R p η p R p,e,ts η p,e,ts p 0,in N/m M S Ramaiah School of Advanced Studies, Bengaluru 40
41 Turbine Design alculations RMD50 Nozzle Outlet Velocity: The following parameters have been calculated: Blade speed = 3.0 m/s ; Work coefficient, = ; Nozzle angle = 70 u, ψu tan 70 φ r, u r, r, r, tan m/s cos70 g c 5 RT 0 r, m/s * 800 with R M p M S Ramaiah School of Advanced Studies, Bengaluru 4
42 Turbine Design alculations RMD50 p R ρ 0 M 37 ρ R. st p ρ , kg/m ρst, kg/m 3 The mass flow rate is.04 kg/s Hence, the volume flow rate is.44 m 3 /s, and the enthalpy drop is 880 J/kg. πn V in Specific speed, N s g Δh π c M S Ramaiah School of Advanced Studies, Bengaluru
43 Velocity Function vs Mach Number for Perfect Gases RMD50 M S Ramaiah School of Advanced Studies, Bengaluru 43
44 Exit Width to Diameter Ratio RMD50 The optimum specific speed for radial-inflow turbine is about The specific speed of this turbine is high. We might expect that there might be a problem arriving at an exducer in which the outlet diameter reduce. Turbine inlet blade width to diameter ratio is calculated using the relation b d b d 5 5 N N s s tan α 4πψ tan α 4π c c5 ψ ψ 3 tan 70 4π N s tan α 4π c ψ 069. M S Ramaiah School of Advanced Studies, Bengaluru 44
45 Optimum Specific Speed RMD50 Distribution of losses along envelope of maximum total-to-static efficiency (Rohlik 968) Typical performance of radial turbine (Rohlik 968) M S Ramaiah School of Advanced Studies, Bengaluru 45
46 Turbine Design alculations RMD50 Outlet Static Density: The outlet static pressure is specified together with the stagnation temperature. The Mach number here is low, and it will be sufficiently accurate to guess the static temperature. 5 p st, 6. 0 N/m T K T 0, 6 st, 6 ρ st, 6 ρ 75 K ρ 57 st, 5 st, 6. guess kg/m M S Ramaiah School of Advanced Studies, Bengaluru 46
47 Results RMD50 The results of the calculations, made for an exducer hub-shroud ratio of 0.3, are tabulated below: W W hb,6 5 d d αw,sh, 6 tan sh, 6 5 x, 6 r, 5 φ Degrees Λ d d φ Degrees tan sh, αw,hb, x, 5 M S Ramaiah School of Advanced Studies, Bengaluru 47
48 Diameter Ratio RMD50 The diameter ratio and the relative flow acceleration are both marginal at 0.8 velocity ratio. Both are satisfactory at a velocity ratio of 0.9. d sh, We select d 5 The flow angles give a guide to the exducer blade angles. The exducer angles should be set to somewhat higher values to allow for flow deviation. An approximate estimate of this deviation would be 3º at the shroud and 5º at the hub. M S Ramaiah School of Advanced Studies, Bengaluru 48
49 Turbine Hub and Tip Dimensions RMD50 d sh, * mm d hb, 6 d d hb,6 sh, π Ψ 3 4 N πφ s mm b d b mm M S Ramaiah School of Advanced Studies, Bengaluru 49
50 Data for Modeling the ompressor RMD50 Inlet Velocity Triangle At Shroud At Hub u hb, x,hb, w,hb, W hb, u sh, =9.65 m/s x,sh, = 7.3 m/s W sh, = 30. w,sh, = 56.4º u hb, = 4.98 m/s x,hb, = 7.3 m/s W hb, = 7.53 w,hb, = 4.º M S Ramaiah School of Advanced Studies, Bengaluru 50
51 Data for Modeling the ompressor RMD50 Outlet Velocity Triangle =350 m/s =7.3 m/s =36.6 m/s =74. m/s =37. m/s m/s M S Ramaiah School of Advanced Studies, Bengaluru 5
52 Data for Modeling Turbine RMD50 Inlet Velocity Triangle act 5 =76.89 m/s c =70 5 w5 w5 =8.68 W 5 =07.95 m/s r,5= U 5 =3.0 m/s M S Ramaiah School of Advanced Studies, Bengaluru 5
53 Modeling Using FX RMD50 reating a Blade: Radial Impeller onfiguration Initial Angle/Thickness Dialog M S Ramaiah School of Advanced Studies, Bengaluru 53
54 Geometric Model - ompressor RMD50 Input Parameters: Blade D sh =4mm D hb = 8.5 mm D =5mm D 3 =30mm Fluid Domain = 30 Z = 0 M S Ramaiah School of Advanced Studies, Bengaluru 54
55 Geometric Model - ompressor RMD50 Blade Fluid Domain Input Parameters: D sh =mm D hb = 5.5 mm D 5 =30mm c5 =70 Z=9 M S Ramaiah School of Advanced Studies, Bengaluru 55
56 3-D AD Models RMD50 ompressor Turbine M S Ramaiah School of Advanced Studies, Bengaluru 56
57 Session Summary RMD50 A procedure for design of radial turbines based on optimum specific speed is discussed. Salient constructional features and working principle of a turbocharger are presented. The design of radial machines is explained through step by step design of compressor and radial turbine modules of a typical turbocharger M S Ramaiah School of Advanced Studies, Bengaluru 57
Lect-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 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 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 informationDesign of Multistage Turbine
Turbomachinery Lecture Notes 7-9-4 Design of Multistage Turbine Damian Vogt Course MJ49 Nomenclature Subscripts Symbol Denotation Unit c Absolute velocity m/s c p Specific heat J/kgK h Enthalpy J/kg m&
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 informationProf. Dr.-Ing. F.-K. Benra. ISE batchelor course
University Duisburg-Essen Campus Duisburg Faculty of engineering Science Department of Mechanical Engineering Examination: Fluid Machines Examiner: Prof. Dr.-Ing. F.-K. Benra Date of examination: 06.03.2006
More informationLect-33. In this lecture... Tutorial on centrifugal compressors. Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Let- 33 In this leture... Let-33 utorial on entrifugal ompressors Problem # At the inlet of a entrifugal ompressor eye, the relative Mah number is to be limited to 0.97. he hub-tip radius ratio of the
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 informationRadial Compressors. Damian Vogt Course MJ2429. Nomenclature
Turbomachinery Lecture Notes 1 007-10-04 Radial Compressors Damian Vogt Course MJ49 Nomenclature Subscripts Symbol Denotation Unit c Absolute velocity m/s h Enthalpy J/kg m& Mass flow rate kg/s r Radius
More informationProf. Dr.-Ing. F.-K. Benra. ISE Bachelor Course
University Duisburg-Essen Campus Duisburg Faculty of Engineering Science Department of Mechanical Engineering Name Matr.- Nr. Examination: Fluid Machines Examiner: Prof. Dr.-Ing. F.-K. Benra Date of examination:
More informationEFFECT OF FORCED ROTATING VANELESS DIFFUSERS ON CENTRIFUGAL COMPRESSOR STAGE PERFORMANCE
Journal of Engineering Science and Technology Vol. 6, No. 5 (2011) 558-574 School of Engineering, Taylor s University EFFECT OF FORCED ROTATING VANELESS DIFFUSERS ON CENTRIFUGAL COMPRESSOR STAGE PERFORMANCE
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 informationAkshay Khadse, Lauren Blanchette, Mahmood Mohagheghi, Jayanta Kapat
Impact of S-CO2 Properties on Centrifugal Compressor Impeller: Comparison of Two Loss Models for Mean Line Analyses The Supercritical CO2 Power Cycles Symposium 2016 Akshay Khadse, Lauren Blanchette, Mahmood
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 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 informationAxial Flow and Radial Flow Gas Turbines
7 Axial Flow and Radial Flow Gas Turbines 7.1 INTRODUCTION TO AXIAL FLOW TURBINES The axial flow gas turbine is used in almost all applications of gas turbine power plant. Development of the axial flow
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 informationOptimization of the blade trailing edge geometric parameters for a small scale ORC turbine
IOP Conference Series: Materials Science and Engineering OPEN ACCESS Optimization of the blade trailing edge geometric parameters for a small scale ORC turbine To cite this article: L Zhang et al 013 IOP
More informationJournal of Mechatronics, Electrical Power, and Vehicular Technology
J. Mechatron. Electr. Power Veh. Technol 06 (2015) 39 8 Journal of Mechatronics, Electrical Power, and Vehicular Technology e-issn:2088-6985 p-issn: 2087-3379 www.mevjournal.com GEOMETRY ANALYSIS AND EFFECT
More informationSmall Scale Axial Turbine Preliminary Design and Modelling
Small Scale Axial Turbine Preliminary Design and Modelling Shadreck M. Situmbeko University of Botswana, Gaborone, Botswana; University of KwaZulu-Natal, Durban, RSA; Freddie L. Inambao University of KwaZulu-Natal,
More informationENERGY TRANSFER BETWEEN FLUID AND ROTOR. Dr. Ir. Harinaldi, M.Eng Mechanical Engineering Department Faculty of Engineering University of Indonesia
ENERGY TRANSFER BETWEEN FLUID AND ROTOR Dr. Ir. Harinaldi, M.Eng Mechanical Engineering Department Faculty of Engineering University of Indonesia Basic Laws and Equations Continuity Equation m m ρ mass
More informationIMPLEMENTATION OF ONE-DIMENSIONAL CENTRIFUGAL COMPRESSOR DESIGN CODE
Copyright 010 by ABCM IMPLEMENTATION OF ONE-DIMENSIONAL CENTRIFUGAL COMPRESSOR DESIGN CODE Elkin I. Gutiérrez Velásquez, elking@unifei.edu.br Marco A.R. Nascimento, marcoantonio@unifei.edu.br Universidade
More informationTurbomachinery Aerodynamics Prof. Bhaskar Roy Prof. A M Pradeep Department of Aerospace Engineering Indian Institute of Technology, Bombay
Turbomachinery Aerodynamics Prof. Bhaskar Roy Prof. A M Pradeep Department of Aerospace Engineering Indian Institute of Technology, Bombay Lecture No. # 26 Tutorial 4: 3D Flows in Axial Flow Turbines We
More informationmywbut.com Hydraulic Turbines
Hydraulic Turbines Hydro-electric power accounts for up to 0% of the world s electrical generation. Hydraulic turbines come in a variety of shapes determined by the available head and a number of sizes
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 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 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 - 21 Centrifugal Compressor Part I Good morning
More informationREVERSE ENGINEERING OF A MICRO TURBOJET ENGINE. Onur Tuncer and Ramiz 0mür İçke Istanbul Technical University Istanbul, Turkey
6. ANKARA INTERNATIONAL AEROSPACE CONFERENCE 14-16 September 2011 - METU, Ankara TURKEY REVERSE ENGINEERING OF A MICRO TURBOJET ENGINE Onur Tuncer and Ramiz 0mür İçke Istanbul Technical University Istanbul,
More informationTheory of turbo machine Effect of Blade Configuration on Characteristics of Centrifugal machines. Unit 2 (Potters & Wiggert Sec
Theory of turbo machine Effect of Blade Configuration on Characteristics of Centrifugal machines Unit (Potters & Wiggert Sec. 1..1, &-607) Expression relating Q, H, P developed by Rotary machines Rotary
More information3 Energy Exchange in Turbomachines
3 Energy Exchange in Turbomachines Problem 1 The solved and unsolved examples of this chapter are meant to illustrate the various forms of velocity triangles and the variety of the turbomachines. In addition,
More informationLecture-10 Tutorial -2 Solved Problems and Tutorial Problems On Three Dimensional flow in Axial Flow Compressor
1 Lecture-10 Tutorial -2 Solved Problems and Tutorial Problems On Three Dimensional flow in Axial Flow Compressor 2 Recap of simple 3-D flow theories (These are mainly used for design) Lect-10 1)Free Vortex
More informationJet Aircraft Propulsion Prof. Bhaskar Roy Prof. A.M. Pradeep Department of Aerospace Engineering
Jet Aircraft Propulsion Prof. Bhaskar Roy Prof. A.M. Pradeep Department of Aerospace Engineering Indian Institute of Technology, IIT Bombay Module No. # 01 Lecture No. # 08 Cycle Components and Component
More informationDynamic centrifugal compressor model for system simulation
Journal of Power Sources xxx (2005) xxx xxx Dynamic centrifugal compressor model for system simulation Wei Jiang, Jamil Khan, Roger A. Dougal Department of Mechanical Engineering, University of South Carolina,
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 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 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 informationIntroduction to Fluid Machines (Lectures 49 to 53)
Introduction to Fluid Machines (Lectures 49 to 5) Q. Choose the crect answer (i) (ii) (iii) (iv) A hydraulic turbine rotates at N rpm operating under a net head H and having a discharge Q while developing
More informationSimple, stable and reliable modeling of gas properties of organic working fluids in aerodynamic designs of turbomachinery for ORC and VCC
IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Simple, stable and reliable modeling of gas properties of organic working fluids in aerodynamic designs of turbomachinery for
More informationA NEW METHOD FOR PREDICITING THE PERFORAMNCE MAP OF A SINGLE STAGE OF A CENTRIFUGAL COMPRESSOR
Proceedings of the 1st Global Power and Propulsion Forum GPPF 2017 Jan 16-18, 2014, Zurich, Switzerland www.pps.global GPPF-2017-119 A NEW METHOD FOR PREDICITING THE PERFORAMNCE MAP OF A SINGLE STAGE OF
More informationInverse Design of Centrifugal Compressor Stages Using a Meanline Approach
Rotating Machinery, 10: 75 84, 2004 Copyright c Taylor & Francis Inc. ISSN: 1023-621X print DOI: 10.1080/10236210490258106 Inverse Design of Centrifugal Compressor Stages Using a Meanline Approach Yuri
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 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 informationThe Turbofan cycle. Chapter Turbofan thrust
Chapter 5 The Turbofan cycle 5. Turbofan thrust Figure 5. illustrates two generic turbofan engine designs. The upper figure shows a modern high bypass ratio engine designed for long distance cruise at
More information1D AND 3D TOOLS TO DESIGN SUPERCRITICAL CO 2 RADIAL COMPRESSORS: A COMPARISON
1D AND 3D TOOLS TO DESIGN SUPERCRITICAL CO 2 RADIAL COMPRESSORS: A COMPARISON B. Monje *, D. Sánchez *, M. Savill, P. Pilidis and T. Sánchez * * Thermal Power Group (GMTS) School of Engineering, University
More informationTheory 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 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 informationDESIGN OF A CENTRIFUGAL COMPRESSOR FOR NATURAL GAS
DESIGN OF A CENTRIFUGAL COMPRESSOR FOR NATURAL GAS S. K. Kurauchi a, and J. R. Barbosa b a Instituto Tecnológico de Aeronáutica Divisão de Engenharia Mecânica Departamento de Turbomáquinas São José dos
More informationA UNIFORM APPROACH TO CONCEPTUAL DESIGN OF AXIAL TURBINE / COMPRESSOR FLOW PATH
The Future of Gas Turbine Technology rd International Conference - October 006, Brussels, Belgium A UNIFORM APPROACH TO CONCEPTUAL DESIGN OF AXIAL TURBINE / COMPRESSOR FLOW PATH Leonid Moroz, Yuri Govorushchenko,
More informationResearch Article Design and Performance Evaluation of a Very Low Flow Coefficient Centrifugal Compressor
International Journal of Rotating Machinery Volume 213, Article ID 293486, 12 pages http://dx.doi.org/1.1155/213/293486 Research Article Design and Performance Evaluation of a Very Low Flow Coefficient
More informationTurbomachinery. Hasan Ozcan Assistant Professor. Mechanical Engineering Department Faculty of Engineering Karabuk University
Turbomachinery Hasan Ozcan Assistant Professor Mechanical Engineering Department Faculty of Engineering Karabuk University Introduction Hasan Ozcan, Ph.D, (Assistant Professor) B.Sc :Erciyes University,
More informationModeling and Validation of the SR-30 Turbojet Engine
Modeling and Validation of the SR-30 Turbojet Engine Thermal Energy Technology 6. Semester Group TE6-604 Aalborg University Title: Modeling and Validation of the SR-30 Turbojet Engine Semester: 6. Semester
More informationDr. S. Ramachandran Prof. R. Devaraj. Mr. YVS. Karthick AIR WALK PUBLICATIONS
Fluid Machinery As per Revised Syllabus of Leading Universities including APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY Dr. S. Ramachandran Prof. R. Devaraj Professors School of Mechanical Engineering Sathyabama
More informationFLOW PATTERN STUDY OF A CENTRIFUGAL PUMP USING CFD METHODS CONCENTRATING ON VOLUTE TONGUE ROLE
FLOW PATTERN STUDY OF A CENTRIFUGAL PUMP USING CFD METHODS CONCENTRATING ON VOLUTE TONGUE ROLE N. Pourmahmoud and S. Majid Taleby Faculty of Engineering, Urmia University, Urmia, Iran E-Mail: majid.taleby@gmail.com
More informationSemi-Empirical Modeling of Small Size Radial Turbines for Refrigeration Purpose
Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 006 Semi-Empirical Modeling of Small Size Radial Turbines for Refrigeration Purpose Gleyzer
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 informationDesign optimization of a centrifugal pump impeller and volute using computational fluid dynamics
IOP Conference Series: Earth and Environmental Science Design optimization of a centrifugal pump impeller and volute using computational fluid dynamics To cite this article: J H Kim et al 2012 IOP Conf.
More informationExercise 8 - Turbocompressors
Exercise 8 - Turbocompressors A turbocompressor TC) or turbocharger is a mechanical device used in internal combustion engines to enhance their power output. The basic idea of a TC is to force additional
More informationCHAPTER EIGHT P U M P I N G O F L I Q U I D S
CHAPTER EIGHT P U M P I N G O F L I Q U I D S Pupmps are devices for supplying energy or head to a flowing liquid in order to overcome head losses due to friction and also if necessary, to raise liquid
More informationIJREAS Volume 2, Issue 2 (February 2012) ISSN:
DESIGN AND CFD ANALYSIS OF SINGLE STAGE, END SUCTION, RADIAL FLOW CENTRIFUGAL PUMP FOR MINE DEWATERING APPLICATION Swapnil Urankar * Dr. H S Shivashankar ** Sourabh Gupta *** ABSTRACT Heavy centrifugal
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 informationChapter three. Two-dimensional Cascades. Laith Batarseh
Chapter three Two-dimensional Cascades Laith Batarseh Turbo cascades The linear cascade of blades comprises a number of identical blades, equally spaced and parallel to one another cascade tunnel low-speed,
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 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 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 informationJet Aircraft Propulsion Prof. Bhaskar Roy Prof A M Pradeep Department of Aerospace Engineering Indian Institute of Technology, Bombay
Jet Aircraft Propulsion Prof. Bhaskar Roy Prof A M Pradeep Department of Aerospace Engineering Indian Institute of Technology, Bombay Module No. #01 Lecture No. # 07 Jet Engine Cycles For Aircraft propulsion
More informationDYNAMIC STRESS MEASUREMENT OF CENTRIFUGAL COMPRESSOR IMPELLER AND STUDY FOR STRENGTH CRITERIA BASED ON CORRELATION BY UNSTEADY CFD
DYNAMIC STRESS MEASUREMENT OF CENTRIFUGAL COMPRESSOR IMPELLER AND STUDY FOR STRENGTH CRITERIA BASED ON CORRELATION BY UNSTEADY CFD by Atsushi Higashio Senior Engineer Hiroyuki Yamashita Research Engineer
More informationTheory of turbo machinery / Turbomaskinernas teori. Dixon, chapter 7. Centrifugal Pumps, Fans and Compressors
Theory of turbo machinery / Turbomaskinernas teori Dixon, chapter 7 Centrifugal Pumps, Fans and Compressors And to thy speed add wings. (MILTON, Paradise Lost.) What do radial machines look like? Swept
More information9. Pumps (compressors & turbines) Partly based on Chapter 10 of the De Nevers textbook.
Lecture Notes CHE 31 Fluid Mechanics (Fall 010) 9. Pumps (compressors & turbines) Partly based on Chapter 10 of the De Nevers textbook. Basics (pressure head, efficiency, working point, stability) Pumps
More informationInternational ejournals
Available online at www.internationalejournals.com International ejournals International ejournal of Mathematics and Engineering 170 (2012) 1603 1612 Design and Coupled Field Analysis of First Stage Gas
More informationIX. COMPRESSIBLE FLOW. ρ = P
IX. COMPRESSIBLE FLOW Compressible flow is the study of fluids flowing at speeds comparable to the local speed of sound. This occurs when fluid speeds are about 30% or more of the local acoustic velocity.
More informationCentrifugal Machines Table of Contents
NLNG Course 017 Table of Contents 1 Introduction and Basic Principles... 1.1 Hydraulic Machines... 1.... 1.3 Pump Geometry... 1.4 Pump Blade Geometry...3 1.5 Diffusers...5 1.6 Pump Losses...6 1.7 Example
More informationCHARACTERIZING THE PERFORMANCE OF THE SR-30 TURBOJET ENGINE
003-1397 CHARACTERIZING THE PERFORMANCE OF THE SR-30 TURBOJET ENGINE T. Witkowski, S. White, C. Ortiz Dueñas, P. Strykowski, T. Simon University of Minnesota Introduction What?!! exclaimed one student.
More informationAxial-Flow Compressor Performance Prediction in Design and Off-Design Conditions through 1-D and 3-D Modeling and Experimental Study
Journal of Applied Fluid Mechanics, Vol. 9, No. 5, pp. 2149-2160, 2016. Available online at www.jafmonline.net, ISSN 1735-3572, EISSN 1735-3645. DOI: 10.18869/acadpub.jafm.68.236.25222 Axial-Flow Compressor
More informationASSESSMENT OF DESIGN METHODOLOGY AND THREE DIMENSIONAL NUMERICAL (CFD) ANALYSIS OF CENTRIFUGAL BLOWER
ASSESSMENT OF DESIGN METHODOLOGY AND THREE DIMENSIONAL NUMERICAL (CFD) ANALYSIS OF CENTRIFUGAL BLOWER D. R. Chaudhari 1, H. N. Patel 2 1,2 Mechanical Department, Government Engineering College Dahod, (India)
More informationNon-Dimensional Aerodynamic Design of Centrifugal Compressor for Small Scale Samkit V Shah 1 Prof. Nilesh R.Sheth 2 Prof. Samip P.
IJSRD - International Journal for Scientific Research & Development Vol. 3, Issue 03, 2015 ISSN (online): 2321-0613 Non-Dimensional Aerodynamic Design of Centrifugal Compressor for Small Scale Samkit V
More informationUNIFIED DESIGN AND COMPARATIVE PERFORMANCE EVALUATION OF FORWARD AND BACKWARD CURVED RADIAL TIPPED CENTRIFUGAL FAN
Proceedings of the International Conference on Mechanical Engineering 3 (ICME3) 6-8 December 3, Dhaka, Bangladesh ICME3-FL- UNIFIED DESIGN AND COMPARATIVE PERFORMANCE EVALUATION OF FORWARD AND BACKWARD
More informationTHE DESIGN OF A FAMILY OF PROCESS COMPRESSOR STAGES
Paper ID: ETC017-134 Proceedings of 1th European Conference on Turbomachinery Fluid dynamics & Thermodynamics ETC1, April 3-7, 017; Stockholm, Sweden THE DESIGN OF A FAMILY OF PROCESS COMPRESSOR STAGES
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 informationConservation of Angular Momentum
10 March 2017 Conservation of ngular Momentum Lecture 23 In the last class, we discussed about the conservation of angular momentum principle. Using RTT, the angular momentum principle was given as DHo
More informationCENTRIFUGAL COMPRESSOR MODELING DEVELOPMENT AND VALIDATION FOR A TURBOCHARGER COMPONENT MATCHING SYSTEM CHRISTOPHER ERIK ERICKSON
CENTRIFUGAL COMPRESSOR MODELING DEVELOPMENT AND VALIDATION FOR A TURBOCHARGER COMPONENT MATCHING SYSTEM by CHRISTOPHER ERIK ERICKSON B.S., Kansas State University, 006 A THESIS submitted in partial fulfillment
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 - 07 Analysis of Force on the Bucket of Pelton
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 - 09 Introduction to Reaction Type of Hydraulic
More informationHydraulic Turbines. Table 6.1 Parameters of hydraulic turbines. Power P (kw) Speed N (rpm)
6 Hydraulic Turbines Problem 1 There are 10 solved examples and 7 exercise problems (exclude Problems 1, 2, and 10) in this chapter. Prepare a table to mention the values of all the parameters, such as
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 informationPreliminary design of a centrifugal turbine for ORC applications
ORC 2011 First International Seminar on ORC Power Systems TU Delft, The Netherlands, 22-23 September 2011 Preliminary design of a centrifugal turbine for ORC applications M. Pini 1, G. Persico 1, E. Casati
More informationHelsinki University of Technology Laboratory of Applied Thermodynamics/CFD-Group. MEMO No CFD/TERMO DATE: November 21, 1997
Helsinki University of Technology Laboratory of Applied Thermodynamics/CFD-Group MEMO No CFD/TERMO-22-97 DATE: November 21, 1997 TITLE GRV-60 Impeller with airfoil-type and unvaned diffusor AUTHOR(S) Harri
More informationDraft Paper-GT
Proceedings of ASME Turbo Expo 2008 Power of Land, Sea, and Air June 9-13, 2008, Berlin, Germnay Draft Paper-GT2008-51033 Optimum design and sensitivity analysis of axial flow compressor with combination
More informationPropellers and Ducted Fans
Propellers and Ducted Fans Session delivered by: Prof. Q. H. Nagpurwala 1 To help protect your privacy, PowerPoint prevented this external picture from being automatically downloaded. To download and display
More informationSpecific Static rotor work ( P P )
The specific Static Rotor ork p 1 ρ Specific Static rotor work ( P P ) here P, P static pressures at points, (P P ) static pressure difference of the rotor ρ density, in case of a compressible medium average
More informationEXPLORING THE DESIGN SPACE OF THE SCO2 POWER CYCLE COMPRESSOR
The 4th International Symposium - Supercritical CO2 Power Cycles September 9-10, 2014, Pittsburgh, Pennsylvania EXPLORING THE DESIGN SPACE OF THE SCO2 POWER CYCLE COMPRESSOR Benjamín Monge Postdoc researcher
More informationRadial Equilibrium Example
An Internet Book on Fluid Dynamics Radial Equilibrium Example For the purposes of this example of a radial equilibrium solution, the flow through the pump impeller is subdivided into streamtubes, as shown
More informationIn this lecture... Axial flow turbine Impulse and reaction turbine stages Work and stage dynamics Turbine blade cascade
Lect- 0 1 Lect-0 In this lecture... Axial flow turbine Ipulse and reaction turbine stages Work and stage dynaics Turbine blade cascade Lect-0 Axial flow turbines Axial turbines like axial copressors usually
More informationON THE THERMODYNAMICS OF ANGULAR PROPULSION
HEFAT2014 10 th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics 14 16 July 2014 Orlando, Florida ON THE THERMODYNAMICS OF ANGULAR PROPULSION Polihronov J.G.*, Straatman A.G.
More informationAerodynamic loading acting on the stator vane in the variable nozzle turbine flow
Applied and Computational Mechanics 9 (2015) 79 95 Aerodynamic loading acting on the stator vane in the variable nozzle turbine flow M. Žatko a, a Faculty of Mechanical Engineering, University of Technology
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 informationTurbomachinery Aero-Thermodynamics
Turbomachinery Aero-Thermodynamics Aero-Energetics 3D Alexis. Giauque 1 1 Laboratoire de Mécanique des Fluides et Acoustique Ecole Centrale de Lyon Ecole Centrale Paris, January-February 2015 Alexis Giauque
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 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 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 information