Fluid Mechanics and Thermodynamics of Turbomachinery, 5e

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128 Fluid Mechanics, Thermodynamics of Turbomachinery C2 a Y W1 C1 C1 W1 -a Y C2 L X L a a (a) X D U W2 D U U W2 U (b) W1 W1 a D Y L X L D Y FIG. 4.25. Velocity and force vectors acting on a blade of a Wells turbine in motion: (a) upward absolute flow onto blade moving at speed U; (b) downward absolute flow onto blade moving at speed U. a a X
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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 238: 102 Fluid Mechanics, Thermodynamics
Page 292: concentric elementary rings, each r
Page 296: and also blade thickness ratio, tur
Page 300: hub-tip ratio, u 1.0 0.8 0.6 0.4 0.
Page 304: C t (a) C P (b) 2.5 2.0 1.5 1.0 0.5
Page 308: U R c x U R a w Axial-flow Turbines
Page 312: arrangements. Also, a full-scale 1.
Page 316: Axial-flow Turbines: Two-dimensiona
Page 320: Axial-flow Turbines: Two-dimensiona
Page 324: CHAPTER 5 Axial-flow Compressors an
Page 328: Axial-flow Compressors and Fans 147
Page 332: of diffusion of kinetic energy in t
Page 336: Reaction ratio For the case of inco
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where tanbm = 1 - 2 (tan b1 + tan b
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Stage pressure rise Consider first
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It is reasonable to take the stage
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Axial-flow Compressors and Fans 159
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(ii) At the operating point i = 0.4
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Flow Axial-flow Compressors and Fan
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Rotating stall and surge Axial-flow
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Tests on low pressure ratio compres
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used. This method can be of use in
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The torque exerted by one blade ele
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Lift coefficient of a fan aerofoil
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(i) a relative Mach number of 0.7 o
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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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