Handbook of Turbomachinery Second Edition Revised - Ventech!

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Surface Curvature Curvature plays a very important role in achieving required film-cooling effectiveness. For the same blowing rate ðM ¼ 0:5Þ, the suction-side effectiveness is higher than that for an equivalent flat plate by up to 100%; on the pressure side the cooling effectiveness is reduced by around 50%. The effect is evident for all coolant-to-gas density ratios. The observed curvature effects on film-cooling effectiveness have been attributed to the balance of the forces exerted on the injected fluid jet by the static pressure and the centrifugal force along the path of the injected jet. These forces have been shown, for low-momentum jets, to act on the injected jet in the direction that moves the jet toward the surface on the suction side and away from the surface on the pressure side. For high-momentum jets, the opposite occurs. Hence, for low-momentum jets, the general trend for film-cooling effectiveness is low on the pressure side and high on the suction side, relative to a flat plate. These trends are reversed for high-momentum jets. Suction surface data exhibited the characteristic limiting value caused by blow-off and observed with flat-plate data. Clearly then, it is necessary for the turbine cooling designer to have a sufficiently large database or appropriately calibrated numerical methods to be able to assess the impact of film cooling during the design process. Pressure Gradient Very little data are available to define the effect of pressure gradient on filmcooling performance. Its effect is generally combined with surface curvature when airfoils are tested under simulated main-stream conditions. In this situation it is not possible to separate the two interrelated effects. However, it is generally understood that both favorable (accelerating) and adverse (decelerating) main-stream pressure gradients can cause a slight degradation of film-cooling effectiveness as compared to that for zero main-stream pressure gradient flow (constant velocity). Main-Stream Turbulence Early studies on film cooling were all performed under low free-stream turbulence conditions. In an actual gas turbine, airfoils experience combustor-generated turbulence as well as the unsteady wake effect generated by upstream airfoil trailing edges. These effects have received more attention in recent years because the results obtained under lowturbulence conditions may lead to significant overprediction of the filmcooling effectiveness. Free-stream turbulence and unsteady wake may damage the film protection on a surface due to greater mixing of the injected Copyright © 2003 Marcel Dekker, Inc.
coolant flow with the main stream, resulting in reduced film-cooling effectiveness. In addition, free-stream turbulence and unsteady wake may increase heat-transfer coefficients, causing further increases in heat transfer to the surface. Experimental data indicate that increased main-stream turbulence reduces the effectiveness of films that often depends on the blowing ratio. Optimum blowing ratio for high turbulence levels were found to be much higher and wider in range than is reported for the lowturbulence level. The data show that film effectiveness for low blowing ratio decreases dramatically in the region close to injection with increasing mainstream turbulence. The effect is reduced at higher blowing ratios. Downstream from injection, film effectiveness is reduced with increasing turbulence for all blowing ratios studied. A very important consideration when looking at film cooling of an airfoil is to ensure that an adequate margin exists between the internal pressure supplying the film cooling air and the local external static pressure at the film injection point. This is to avoid the possibility of hot gas ingestion into the airfoil. The amount by which the film air supply pressure exceeds the exit pressure is usually referred to as the ‘‘backflow margin.’’ Among other important effects of film cooling that the designer must consider are momentum losses associated with mixing of the coolant with the main-stream flow and its effects on turbine aerodynamic performance. Considering the complexity of film-cooling interaction with the main stream and the large number of factors affecting film-cooling effectiveness, it is recommended to validate turbine airfoil film-cooling design data in cascades where geometry, Reynolds number, Mach number, coolant-to-main-stream density and temperature ratios, and main-stream turbulence are all closely simulated to represent engine design conditions. The available literature can be used for guidance in these tests. Film-Cooling Slots Trailing-edge pressure-side slots, often replacing traditional (in the past) trailing-edge ejection, is the most common application of slots (often shaped as gill slots). They provide an improvement in the turbine aerodynamic efficiency by allowing the trailing-edge thickness to be reduced. Even though an increase in cooling flow is required for the pressure-side slots to achieve the same metal temperature, the reduction in trailing-edge thickness still produces a net performance improvement. With this configuration, the temperature of the trailing-edge region depends strongly on the heattransfer coefficient and the film effectiveness in the area downstream of the slot exit. Copyright © 2003 Marcel Dekker, Inc.
Page 1 and 2:
D E K K E R Handbook of Turbomachin
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MECHANICAL ENGINEERING A Series of
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61 Computer-Aided Simulation in Rai
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127 Designing for Product Sound Qua
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Preface to the Second Edition The o
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Preface to the Second Edition Prefa
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Contributors Nathan G. Adams The Bo
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1 Introduction Earl Logan, Jr.*, an
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HISTORICAL BACKGROUND Earl Logan, J
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MECHANICAL AND THERMAL DESIGN CONSI
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Figure 1 Cross-section showing the
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Figure 2 Turboprop engine, TPE 331-
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Figure 4 Auxiliary power unit, APU1
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Durability. The mechanical and ther
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with time during flight. Such a typ
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experience and existing similar des
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adverse pressure gradient against w
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and its attachments. A substantial
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Figure 9 Typical high-pressure turb
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and the measurement of local heat-t
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due to cyclic operation. In additio
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the steady and transient conditions
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Table 3(a) Steps in a Three-Dimensi
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Figure 16 Schematic Goodman diagram
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occur due to particles of unburned
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pressures at critical points. These
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1. Ceramics are subject to ‘‘in
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with Transient Tests and Surface Co
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Overall engine performance goals tr
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Much of the complexity of turbomach
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End-wall boundary layers can also h
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pressure at the wake centerline. Th
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the same vaneless diffuser and shro
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from internal cooling passages, thr
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Further downstream, the wake was ev
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to its original position. This unst
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cooling film was found to trip the
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shroud static pressure and the exit
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stage in the design process allows
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Flow Physics Modeling Modeling of t
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passage to the next, assuming that
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The next step in modeling accuracy
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tend to be large, due to the necess
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Navier-Stokes equations are time-ma
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To satisfy these requirements, it i
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are discussed by a number of author
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source code, and to assign each seg
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selected locations in the flow path
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of the component designers must be
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Trends in Flow Modeling Capabilitie
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optimize the flow behavior. The eff
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20. D. Eckardt, ‘‘Flow Field An
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49. K. R. Kirtley, ‘‘An Algebra
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INTRODUCTION 3 Turbine Gas-Path Hea
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Figure 1 Maximum turbine rotor inle
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Figure 2 Intersecting S1 and S2 sur
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determination. Nothing in the simpl
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e well matched with the engine. The
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case different forms of the popular
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volume will be equal to the accumul
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Figure 9 Nusselt number vs. vane su
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Furthermore, to keep computer time
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Figure 12 Comparison of three turbu
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and small and cooled and uncooled t
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Figure 15 Miniature heat flux gauge
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Figure 17 Time resolved heat transf
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Figure 19 Surface pressure changes
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NONUNIFORM INLET FLOW All gas turbi
Page 137 and 138: Figure 22 Typical distributions of
Page 139 and 140: 4. Better instrumentation for heat-
Page 141 and 142: 24. R. H. Ni, ‘‘A Multiple Grid
Page 143 and 144: 4 Selection of a Gas Turbine Coolin
Page 145 and 146: Re L ¼ rVL=m—Reynolds number bas
Page 147 and 148: (1,300 8F). But modern gas turbines
Page 149 and 150: during engine operation are compati
Page 151 and 152: Figure 3 Airfoil cooling techniques
Page 153 and 154: expected to increase this limit to
Page 155 and 156: 1. Reduce the effect of main-stream
Page 157 and 158: P? is total inlet pressure. Tc=T? i
Page 159 and 160: thereby increasing both the skin-fr
Page 161 and 162: After four decades of advancement i
Page 163 and 164: correspondingly high coolant-side t
Page 165 and 166: component. Use of a hot cascade for
Page 167 and 168: nozzle vanes is limited by their ox
Page 169 and 170: Figure 9 Typical turbine hot sectio
Page 171 and 172: important factor to consider for tr
Page 173 and 174: Figure 10 Evolution of nozzle geome
Page 175 and 176: the exit of the combustor section f
Page 177 and 178: Figure 12 Inlet turbulence effect o
Page 179 and 180: in heat transfer as the Reynolds nu
Page 181 and 182: easonably well using correlations e
Page 183 and 184: in the section on blade cooling tha
Page 185 and 186: mass flow rate (e.g., M ¼ 1 for a
Page 187: holes. Cooling hole pattern is an i
Page 191 and 192: above equation assumes a constant f
Page 193 and 194: Figure 15 Definition of film-coolin
Page 195 and 196: edistribution of the external heat-
Page 197 and 198: Three-Dimensional Effects The three
Page 199 and 200: In order to achieve the bulk metal
Page 201 and 202: coefficient is given by Nud ¼ hd=k
Page 203 and 204: Where G ¼ 2:24ðw=tÞ 0:1 ðReeÞ
Page 205 and 206: pressure drop. The 608/458 V-shaped
Page 207 and 208: Some of the studies have found that
Page 209 and 210: of the cooling air and the turning
Page 211 and 212: Figure 20 Impingement geometry defi
Page 213 and 214: correlated by Nu a d ¼ 0:63ðGd=m
Page 215 and 216: tangentially to the inner wall, beh
Page 217 and 218: The effectiveness of a suction surf
Page 219 and 220: vortex structure. Their studies sho
Page 221 and 222: Figure 23 Effect of preswirler pres
Page 223 and 224: component to the cooling air that c
Page 225 and 226: axial gap. A static pressure variat
Page 227 and 228: Weight, cost, and complexity constr
Page 229 and 230: Figure 28 Effectiveness of liner co
Page 231 and 232: thickness. A problem this poses is
Page 233 and 234: portion of the hole has been shown
Page 235 and 236: unacceptable engine performance pen
Page 237 and 238: analysis, in order to provide accur
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Figure 30 Application of PSP for fi
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thermocouple positioned close to th
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spray-painted black (Hallcrest, BB-
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Figure 32 Schematics of a hot casca
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the turbine static temperature (rot
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Figure 33 Experimental rig for inve
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their color when exposed to higher
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margins defined within each discipl
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them. The larger gas-path divergenc
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Figure 36 Blade-cooling selection d
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8. B. Barry, Turbine Blade Cooling:
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40. A. K. Tolpadi and M. E. Crawfor
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73. R. S. Abhari, ‘‘Comparison
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106. J. M. Owen and R. H. Rogers, F
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138. I. Egorov, G. Kretinin, I. Les
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integrity (stress levels) will have
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Figure 1 Instant entropy contours o
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Aerodynamic Interaction (Unsteady L
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Figure 3 Pitchwise time-averaged en
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The above considerations are all fo
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lades, the wavelength of the distur
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forcing and damping, and hence the
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frequency and its higher harmonics
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The two-cell pattern with a relativ
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Figure 9 Typical blade flutter boun
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field is generated to satisfy the t
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Figure 11 Instant static pressure c
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Figure 12 Calculated instantaneous
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Figure 14 Time-space static pressur
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one period Tp (neglecting change of
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It should be noted that the effects
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There are some further points to no
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Figure 17 Flow around an NACA-65 ai
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(11) for a simple case]: Where WA
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Regardless whether loosely coupled
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Several methods have been developed
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significant difference is introduce
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losses, but it may affect to a mini
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when we refine a mesh in an unstead
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8. W. S. Barankiewicz and M. D. Hat
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6 Fundamentals of Compressor Design
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Figure 3 AlliedSignal 331 turboprop
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each of the selected radii. The pro
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components of gas velocity upstream
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Observe that each of the curves for
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The conservation of angular momentu
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allowable static pressure ratio of
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Figure 7 Boundary layers and wakes
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component that is perpendicular to
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Figure 10 (a) Deflection of flow of
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increase in the downstream pressure
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Mach number at a compressor outlet
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Figure 12 Sketch of flow surface an
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useful shapes and orientations of b
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where G and oa are constant along a
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There is a good reason for this sit
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Projected Shape in Meridional Plane
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inherent flow range of the impeller
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compressors. Multistage centrifugal
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turbines. In these designs the high
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Corrections for Streamline Curvatur
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Preparation of Maps Once the losses
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that circumferential gradients meas
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Nastran, which was developed by NAS
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tests. One should take pains to pro
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e predicted in advance. Total press
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Cv Coefficient of heat at constant
Page 373 and 374:
15. S. Lieblein, J. Basic Eng., Tra
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INTRODUCTION 7 Fundamentals of Turb
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Figure 1 Cross sections of generic
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espectively. Radial-inflow turbines
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Figure 4 Typical rotor blade shapes
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Figure 6 The expansion process acro
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the average for the gas flowing thr
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etween the velocity diagram and the
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gas dynamics relation p 00 p ¼ T 0
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Figure 9 Variations in turbine velo
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pressure, inlet losses are usually
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diffuser recovery, defined as Rp ¼
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different turbines easier, dimensio
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where and y ¼ T 0 in TSTD d ¼ p0
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sizing exercises where the details
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where Rth is the Reynolds number ba
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order to determine the overall turb
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The classical approach to satisfyin
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clearance. Since tip clearance repr
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turbine with an effective diffuser,
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atio ðp 0 in =pdisÞ is 3. The sta
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Automation of Calculations and Trad
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and for the rotor Zrotor ¼ ð0:1Þ
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the energy extracted and the rotor
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RADIAL-INFLOW TURBINE SIZING Differ
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interpolations from existing design
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Glassman [1], the optimum ratio of
Page 427 and 428:
design fault in the radial-inflow t
Page 429 and 430:
[27]. In order to avoid manufacturi
Page 431 and 432:
The rotor exit critical velocity is
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The hub-to-tip radius ratio at the
Page 435 and 436:
REFERENCES 1. A. J. Glassman (ed.),
Page 437 and 438:
8 Steam Turbines Thomas H. McCloske
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Figure 3 Reciprocating steam engine
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This process began in the 1920s, al
Page 443 and 444:
First Law of Thermodynamics The fir
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the amount of fuel burned and the p
Page 447 and 448:
Figure 7 Rankine cycle temperature-
Page 449 and 450:
The Mollier diagram is quite useful
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Figure 10 Theoretical Rankine cycle
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stages of the turbine is at a highe
Page 455 and 456:
calculate the relevant thermodynami
Page 457 and 458:
Figure 14 Steam leakage losses for
Page 459 and 460:
can reveal nozzle and/or blade eros
Page 461 and 462:
Figure 17 Enlarged portion of the M
Page 463 and 464:
Traditionally, pressures have been
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Figure 21 Wetness thermodynamic los
Page 467 and 468:
Figure 23 Radial steam turbine flow
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Figure 25 Percentage stage reaction
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The power output of the stage can b
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the LP turbines is split into paral
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Turbine Inlet Two stages in particu
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of 20%, which would cause excessive
Page 479 and 480:
Figure 30 Typical low-pressure stea
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ductility and poor toughness, since
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‘‘tramp’’ elements to minim
Page 485 and 486:
End Seals End seals or packing glan
Page 487 and 488:
Drains Condensate can form during s
Page 489 and 490:
Figure 32 Steam turbine blade roots
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Figure 34 Cross-section view of thr
Page 493 and 494:
Figure 36 Interblade shroud and Tie
Page 495 and 496:
Where The influence of notch sensit
Page 497 and 498:
Similarly, LP turbine blades are su
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those made of steel. Note, however,
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esult, significant attention must b
Page 503 and 504:
Figure 38 Centrifugal stresses on a
Page 505 and 506:
Figure 39 Centrifugal bending stres
Page 507 and 508:
onto the rotating blade. These can
Page 509 and 510:
Vortex shedding from blade trailing
Page 511 and 512:
Figure 42 Torsional coupled vibrati
Page 513 and 514:
Figure 44 Stall flutter of low-pres
Page 515 and 516:
Start-Stop Transients/Overspeeds La
Page 517 and 518:
(4) ellipiticity, such as caused by
Page 519 and 520:
Figure 47 Campbell diagram (frequen
Page 521 and 522:
Furthermore, in practice each manuf
Page 523 and 524:
Figure 49 Modal diameters of a low-
Page 525 and 526:
Figure 51 Three-dimensional computa
Page 527 and 528:
Figure 52 Converging wedge and resu
Page 529 and 530:
value as the operating value of uv/
Page 531 and 532:
Lubrication Supply System Design De
Page 533 and 534:
Figure 56 Steam turbine oil system
Page 535 and 536:
The main oil reservoir is located b
Page 537 and 538:
Although a light oil does provide a
Page 539 and 540:
temperatures are suspected as reaso
Page 541 and 542:
There is no fixed or absolute value
Page 543 and 544:
pivots incorporated in this bearing
Page 545 and 546:
covers and doors. Pipe scale, rust,
Page 547 and 548:
Figure 63 Mechanical hydraulic cont
Page 549 and 550:
Figure 64 Steam turbine electro-hyd
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Figure 65 Steam turbine electro-hyd
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generator rotor moment of inertia h
Page 555 and 556:
the turbine against overspeed. This
Page 557 and 558:
an additional electronic overspeed
Page 559 and 560:
Figure 68 Steam turbine protective
Page 561 and 562:
3. Need for better understanding of
Page 563 and 564:
REFERENCES 1. J. C. Zink, ‘‘Ste
Page 565 and 566:
No. TWDPS-1, The American Society o
Page 567 and 568:
58. A. V. Sarlashkar and T. C. T. L
Page 569 and 570:
81. IEEE Guide for Abnormal Frequen
Page 571 and 572:
Atlanta, GA, Oct. 18-22, 1992, PWR-
Page 573 and 574:
Performance Enhancement Program, he
Page 575 and 576:
of the design process toward achiev
Page 577 and 578:
procedure capable of addressing mul
Page 579 and 580:
to achieve a specific target pressu
Page 581 and 582:
objective was to minimize the downs
Page 583 and 584:
more closely represents the largest
Page 585 and 586:
temperature by forming a thin film
Page 587 and 588:
such as the one described here. For
Page 589 and 590:
k is the thermal conductivity of th
Page 591 and 592:
through finite differences. Mathema
Page 593 and 594:
Figure 4 Comparison of blade cross-
Page 595 and 596:
integration of multiple disciplines
Page 597 and 598:
17. S. S. Talya, ‘‘Multidiscipl
Page 599 and 600:
INTRODUCTION 10 Rotordynamic Consid
Page 601 and 602:
Figure 1 (c) AlliedSignal 331 turbo
Page 603 and 604:
Figure 2 Rotor system displacements
Page 605 and 606:
Figure 3 Elliptic lateral whirl. av
Page 607 and 608:
vibration (either forward or backwa
Page 609 and 610:
Figure 6 The Laval-Jeffcott rotor.
Page 611 and 612:
are 1808 out of phase (i.e., the be
Page 613 and 614:
this graph is quite simple; however
Page 615 and 616:
included on these types of graphs b
Page 617 and 618:
on the shaft is zero. Thus, the ste
Page 619 and 620:
are uðtÞ ¼e zeott uo cos ott þ
Page 621 and 622:
satisfies the inequality O < ot 1
Page 623 and 624:
Figure 16 Laval-Jeffcott rotor tran
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Figure 18 Whirl speed map: Laval-Je
Page 627 and 628:
Figure 20 Laval-Jeffcott rotor: ste
Page 629 and 630:
Figure 22 Typical precessional mode
Page 631 and 632:
Figure 24 Examples of flexible disk
Page 633 and 634:
ackward modes, however, involve con
Page 635 and 636:
Figure 29 Steady unbalance response
Page 637 and 638:
assist in attenuating high vibratio
Page 639 and 640:
properly sizing the damper, a highl
Page 641 and 642:
Figure 31 Gas turbine schematic and
Page 643 and 644:
Flexible Disk If the frequency of a
Page 645 and 646:
motion for each subsegment to form
Page 647 and 648:
Figure 35 Whirl speed map—straddl
Page 649 and 650:
Figure 37 Rotor-bearing-support str
Page 651 and 652:
DESIGN STRATEGIES AND PROCEDURES Ro
Page 653 and 654:
Figure 38 Straddle mounted rotor. (
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Figure 39 Unbalance response: strad
Page 657 and 658:
Figure 40 Double overhung rotor—d
Page 659 and 660:
earing supports are reduced. The th
Page 661 and 662:
and also increases the critical spe
Page 663 and 664:
Examples of structure modes couplin
Page 665 and 666:
REFERENCES 1. D. Childs, Turbomachi
Page 667 and 668:
section is intended to place today
Page 669 and 670:
pressure-fed propellant systems. Hi
Page 671 and 672:
normally be considered a very small
Page 673 and 674:
increase of required suction perfor
Page 675 and 676:
displaced by the F-1 oxidizer pump
Page 677 and 678:
exposure may be subjected to imping
Page 679 and 680:
the exhaust duct. Sized to create s
Page 681 and 682:
excess of 6,000 psi for consumption
Page 683 and 684:
lifetime. With very few exceptions,
Page 685 and 686:
using hydrocarbon fuel combustion p
Page 687 and 688:
can yield noticeable savings in req
Page 689 and 690:
Figure 3 Rocket engine system schem
Page 691 and 692:
Figure 6 Staged combustion system,
Page 693 and 694:
each stage. The term C0 represents
Page 695 and 696:
Figure 10 Some representative turbo
Page 697 and 698:
emembered that the second (and any
Page 699 and 700:
the greatest demands on turbopump p
Page 701 and 702:
momentum exchange between working f
Page 703 and 704:
Figure 13 Arrangement of various tu
Page 705 and 706:
pressure levels. As long as combust
Page 707 and 708:
Figure 14 Approxmate values of pump
Page 709 and 710:
liquid rocket engine systems, and e
Page 711 and 712:
above becomes a factor. This statem
Page 713 and 714:
We can then state (correctly) that,
Page 715 and 716:
Figure 15c Typical 2-D centrifugal
Page 717 and 718:
have seen that the flow rate throug
Page 719 and 720:
somewhat smaller magnitude of vecto
Page 721 and 722:
general indicator. Nss will give us
Page 723 and 724:
U ¼ rotor tangential velocity. By
Page 725 and 726:
and pump flow derived from the engi
Page 727 and 728:
In addition to shaft seals, shaft b
Page 729 and 730:
should be understood that the optim
Page 731 and 732:
stable operation is assured. In som
Page 733 and 734:
From Eq. (16) an impeller radial ou
Page 735 and 736:
Figure 18 Examples of centrifugal p
Page 737 and 738:
tional to clearance distance) with
Page 739 and 740:
I would like to conclude this secti
Page 741 and 742:
generally result in lower pump hydr
Page 743 and 744:
Figure 15h Cross-section of a typic
Page 745 and 746:
solutions of Eq. (7) for both stage
Page 747 and 748:
Figure 15k H-Q characteristics for
Page 749 and 750:
Figure 15l Typical inducer configur
Page 751 and 752:
camber) is proportionally lower. Th
Page 753 and 754:
Figure 22 Single-stage impulse turb
Page 755 and 756:
the velocity ratio K, but in somewh
Page 757 and 758:
~V and ~n ¼ fluid velocity and con
Page 759 and 760:
Fig. 25. The nature of the flow in
Page 761 and 762:
Although shrouded centrifugal impel
Page 763 and 764:
is a parasitic device, whose flow r
Page 765 and 766:
apidly than does the inducer thrust
Page 767 and 768:
Figure 30 LH2 turbopump rotor mecha
Page 769 and 770:
eplacement of a failed bearing with
Page 771 and 772:
shall see, contemporary rocket engi
Page 773 and 774:
needs of the aircraft gas turbine a
Page 775 and 776:
was increased due to engine upratin
Page 777 and 778:
12 Turbomachinery Performance Testi
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istics. The more accurate the perfo
Page 781 and 782:
Inlet Distortion Most turbomachiner
Page 783 and 784:
Gas Thermodynamic Properties Turbom
Page 785 and 786:
ought to rest isentropically. Total
Page 787 and 788:
include not only the pressure chang
Page 789 and 790:
The circumferential placement of th
Page 791 and 792:
simply arithmetically averaging the
Page 793 and 794:
usually mounted in radial immersion
Page 795 and 796:
Figure 12(b) Radial flow angle prof
Page 797 and 798:
Figure 15 Wake rake total pressure
Page 799 and 800:
Figure 16 Blade-tip pressure traces
Page 801 and 802:
Figure 18 Typical test rig schemati
Page 803 and 804:
INSTRUMENTATION DESIGN CONSIDERATIO
Page 805 and 806:
Dynamic Pressure. Dynamic pressure
Page 807 and 808:
thermocouples. With care in constru
Page 809 and 810:
Figure 24 Typical two-dimensional f
Page 811 and 812:
Thermocouple lead wires should be i
Page 813 and 814:
Corrected Flow The flow rates used
Page 815 and 816:
pressure ratio [15]. It can be calc
Page 817 and 818:
SYMBOLS A Cross-section area Cd Dis
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INTRODUCTION 13 Automotive Supercha
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Figure 2 A Roots-type supercharger
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The supercharger was in routine use
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Table 1 Superchargers Versus Turboc
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1960s, turbocharging was used by US
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Roots Blower The Roots-type blower
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speeds. The sound is caused by the
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Figure 8b How the Ro-charger operat
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The vanes in many designs are preve
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Figure 11a Key components of the G-
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Figure 11c G-Lader supercharger is
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Figure 12b Schematic of centrifugal
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Figure 14b Components of the typica
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Turbine Design The turbine housing
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inertia of the wheel assembly. Mini
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Figure 18 (a) Turbocharger compress
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Theoretically this efficiency is: o
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The overall turbine efficiency incl
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adjust the spring force to vary the
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Figure 22b Two vanes are used to pr
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However, the temperature has to be
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air can reduce carbon monoxide and
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Figure 25 (a) Schematic of the COMP
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this plus the fact that the exhaust
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14 Tesla Turbomachinery Warren Rice
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press at the time of the invention
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can be made to simplify the equatio
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comparison of the results of variou
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y composing them of nested cones ra
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26. E. Bakke, ‘‘Theoretical and
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61. M. Piesche, ‘‘Investigation
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15 Hydraulic Turbines V. Dakshina M
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Table 1 Variables of Interest in Tu
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Figure 1 Variation of impeller shap
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Figure 2 Flow and velocity componen
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Figure 3 Schematic diagram of Pelto
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shown in Fig. 5(see KadambiandPrasa
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classified according to the directi
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The manufacturers of hydraulic turb
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The direction of the relative veloc
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Table 3 Variation of Some Quantitie
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denoted by hd. Thus the efficiency
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Figure 14 Draft tube setting. same
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REFERENCES 1. J. J. Fritz, Small an
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Handbook of Turbomachinery Second Edition Revised - Ventech!

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