Fluid Mechanics and Thermodynamics of Turbomachinery, 5e

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where tanbm = 1 – 2 (tan b1 + tan b2). Now CL = L/( 1 – 2 rw 2 ml) hence, substituting for L above, (5.15) The work done by each moving blade per second is YU <strong>and</strong> is transferred to the fluid through one blade passage during that period. Thus, YU = rscx(h 03 - h 01). Therefore, the stage loading factor may now be written Substituting eqn. (5.15) in eqn. (5.16) the final result is (5.16) (5.17) In Chapter 3, the approximate analysis indicated that maximum efficiency is obtained when the mean flow angle is 45deg. The corresponding optimum stage loading factor at bm = 45deg is (5.18) Since CD
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Fluid Mechanics, Thermodynamics of
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Preface to the Fifth Edition In the
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Preface to the Fourth Edition It is
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Preface to Third Edition Several mo
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List of Symbols A area A2 area of a
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z enthalpy loss coefficient, total
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Contents PREFACE TO THE FIFTH EDITI
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Velocity diagrams of the compressor
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10. Wind Turbines 323 Introduction
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2 Fluid Mechanics, Thermodynamics o
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10 Fluid Mechanics, Thermodynamics
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CHAPTER 2 Basic Thermodynamics, Flu
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CHAPTER 3 Two-dimensional Cascades
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CHAPTER 4 Axial-flow Turbines: Two-
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Page 290: 128 Fluid Mechanics, Thermodynamics
Page 344: Stage pressure rise Consider first
Page 348: It is reasonable to take the stage
Page 352: Axial-flow Compressors and Fans 159
Page 356: (ii) At the operating point i = 0.4
Page 360: Flow Axial-flow Compressors and Fan
Page 364: Rotating stall and surge Axial-flow
Page 368: Tests on low pressure ratio compres
Page 372: used. This method can be of use in
Page 376: The torque exerted by one blade ele
Page 380: Lift coefficient of a fan aerofoil
Page 384: (i) a relative Mach number of 0.7 o
Page 388: CHAPTER 6 Three-dimensional Flows i
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therefore, The thermodynamic relati
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In Chapter 5, reaction in an axial
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vantage is the large amount of roto
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Assuming constant stagnation enthal
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where In the above example, 1 - a/W
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therefore (6.24) For this free-vort
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After differentiating the last term
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(6.38) after combining with eqn. (6
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Three-dimensional Flows in Axial Tu
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velocity undergoes an abrupt change
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adding these to the related radial
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References Adamczyk, J. J. (2000).
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and the axial velocity is constant
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engine turbochargers, chemical plan
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Centrifugal Pumps, Fans and Compres
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or since Since I1 = I2 across the i
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For the inlet geometry shown in Fig
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The required diameter of the eye is
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(Mr1) = mW 2 /(p k p 01 a01 3 ) ·
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(iii) Use of prewhirl at entry to i
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(7.13a) where cq2 is the tangential
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(number of blades). He also found t
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Determining the velocities and head
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efficiencies seldom exceeded 80% gi
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efficiently converting this energy
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Therefore Hence, The diffuser syste
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Dq (deg) 240 160 80 Centrifugal Pum
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(7.41) If choking occurs in the rot
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Van den Braembussche, R. (1985). De
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Assuming that the hydraulic efficie
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Radial Flow Gas Turbines 247 FIG. 8
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Basic design of the rotor Radial Fl
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Radial Flow Gas Turbines 253 (8.9)
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Thus, the total-to-static efficienc
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Now, Loss coefficients in 90deg IFR
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P S P S c 2 Direction of rotation (
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and, combining this with eqns. (8.2
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(ii) Rewriting eqn. (8.26), (iii) U
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Thus, combining eqns. (8.39) and (8
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U 2/c o 0.8 0.7 0.6 88 Radial Flow
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(a) the static pressure at rotor ex
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(a) (2) (1) w 2 b2 ¢ w 2 ¢ b2, op
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Radial Flow Gas Turbines 273 This e
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Radial Flow Gas Turbines 279 occurs
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(a) f = 0.83 a 0 = q 0 U 0 = -7.18
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Measured performance Radial Flow Ga
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Radial Flow Gas Turbines 287 Whitfi
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Radial Flow Gas Turbines 289 Absolu
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Hydraulic Turbines 291 TABLE 9.1. D
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TABLE 9.3. Operating ranges of hydr
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Hydraulic Turbines 295 ridge splits
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Hydraulic Turbines 297 (9.3) (9.4)
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Hydraulic Turbines 299 FIG. 9.8. Me
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Hydraulic Turbines 301 (9.10) The e
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Neglecting bearing and windage loss
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Hydraulic Turbines 305 Figure 9.12
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Hydraulic Turbines 307 It is of int
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Hydraulic Turbines 309 constant. Th
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(a) (b) Hydraulic Turbines 311 FIG.
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TABLE 9.4. Calculated values of flo
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Hydraulic Turbines 315 gave measure
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Hydraulic Turbines 317 using Thoma
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Avoiding cavitation Hydraulic Turbi
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Hydraulic Turbines 321 nozzles. The
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CHAPTER 10 Wind Turbines Take care
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FIG. 10.2. Tower Windmill, Bidston,
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Brake discs Flexible coupling Build
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Small HAWTs Small wind turbines wit
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(iii) no flow rotation produced by
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It is convenient to define an axial
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Example 10.2. Determine the radii o
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where a - T = 0.3262. Sharpe (1990)
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each element must have an associate
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In the actuator disc analysis the v
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operate in post-stall conditions wh
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Solving the equations The foregoing
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Pitch angle, b (deg) 30 20 10 0 0.2
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TABLE 10.4. Data used for summing t
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F 1.0 0.8 0.6 0.4 0.2 0 0.4 dX = 4
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TABLE 10.5. Summary of results for
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Power coefficient, C P 0.6 0.4 0.2
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C X/(JC L) 0.14 0.12 0.10 0.08 0.06
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The flow angle j at optimum power c
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R 1 2 3 8 3 CP = P ( prR cx )= ( -a
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caused by this increased roughness
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Airfoil S820 S819 r/R 0.95 0.75 pro
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Airfoil S817 S816 r/R 0.95 0.75 NRE
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C C 0.4 0.2 -0 -0.2 -0.4 -0.6 twist
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According to Tangler (2002), some l
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understanding of the complex phenom
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References Wind Turbines 375 Abbott
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Bibliography Cumpsty, N. A. (1989).
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APPENDIX 2 Answers to Problems Chap
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Chapter 8 1. 586 m/s, 73.75 deg. 2.
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Index Terms Links Axial flow compre
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Index Terms Links Cascades, two-dim
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Index Terms Links Coefficient of, c
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Index Terms Links Diffusers (Cont.)
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Index Terms Links Francis turbine 2
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Index Terms Links Illustrative exam
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Index Terms Links Mollier diagram,
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Index Terms Links Pressure head 4 P
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Index Terms Links Rotor configurati
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Index Terms Links Thoma’s coeffic
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Index Terms Links U Units Imperial
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