Handbook of Turbomachinery Second Edition Revised - Ventech!

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The pressure ratio represents the actual total pressure ratio from compressor inlet to outlet without including any ducting losses. The ratio is determined by dividing the total (static plus dynamic pressure) absolute pressure at the compressor outlet by the total absolute pressure at the compressor inlet: Where pressure ratio ¼ P2C P1C P1C ¼ compressor inlet air total pressure (in. Hg abs.). P2C ¼ compressor discharge air total passage (in. Hg abs.). The corrected air flow is corrected using a relationship of the form ðmass flow rateÞ6ðabsolute temperatureÞ 1=2 ðpressureÞ For example, a typical correction is Where corrected air flow ¼ 1=2 WaðT1C=545Þ P1C=28:4 T1C ¼ compressor inlet air total temperature (degrees R). W a ¼ compressor discharge air flow (lb/min). Likewise, the compressor speed is corrected using a a correction of the form ðcompressor speedÞ ðtemperatureÞ 1=2 A typical correction is corrected compressor speed ¼ N ðT1C=545Þ 1=2 where N is the compressor speed (rpm). The basis for the adiabatic compression efficiency is an adiabatic compression in which the pressure increases without any thermal loss or gain. However, the temperature increases with increased pressure. This ideal temperature is compared with the actual higher temperature obtained in practice due to energy losses to determine the adiabatic efficiency. Copyright © 2003 Marcel Dekker, Inc.
Theoretically this efficiency is: or Where compressor efficiency ¼ compressor adiabatic efficiency ¼ T1CY isentropic enthalpy rise across compressor stage through compressor pressure ratio actual enthalpy rise across compressor stage T2C T1C T2C ¼ compressor outlet air total temperature (degrees R). Y ¼ðP2C=P1CÞ 0:283 1. There are three main areas on the centrifugal compressor map. The central area is the stable operating zone. The surge line in the low flow rate area at the left of Fig. 18(a) defines an area of pressure and flow rate where compressor operation is unstable. Surging occurs when the mass flow rate through the compressor is reduced while maintaining a constant pressure ratio until a point is reached where local flow reversal occurs in the boundary layers. If the flow rate is further reduced, complete reversal occurs. This will relieve the adverse pressure gradient until a new flow regime is established at a lower pressure ratio. The flow rate will again build up to the initial condition, and this flow instability will continue at a fixed frequency and in some cases can become quite violent. The compressor map shows a tradeoff in compressor design. The narrower the operating range of the compressor, the sharper the surge. However, the broader the range, the lower the peak efficiency. Turbine Performance Map The performance map for the turbine shows the lines of constant corrected speed, corrected exhaust gas flow, and overall turbine efficiency plotted against turbine pressure ratio (Fig. 19). The total-to-static pressure ratio is used here since the actual exit conditions cannot be predicted for a particular installation. Where pressure ratio ðexpansion ratioÞ ¼ P1T P2T P1T ¼ inlet gas total absolute pressure (in. Hg). Copyright © 2003 Marcel Dekker, Inc.
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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
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Figure 22 Typical distributions of
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4. Better instrumentation for heat-
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24. R. H. Ni, ‘‘A Multiple Grid
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4 Selection of a Gas Turbine Coolin
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Re L ¼ rVL=m—Reynolds number bas
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(1,300 8F). But modern gas turbines
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during engine operation are compati
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Figure 3 Airfoil cooling techniques
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expected to increase this limit to
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1. Reduce the effect of main-stream
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P? is total inlet pressure. Tc=T? i
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thereby increasing both the skin-fr
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After four decades of advancement i
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correspondingly high coolant-side t
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component. Use of a hot cascade for
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nozzle vanes is limited by their ox
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Figure 9 Typical turbine hot sectio
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important factor to consider for tr
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Figure 10 Evolution of nozzle geome
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the exit of the combustor section f
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Figure 12 Inlet turbulence effect o
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in heat transfer as the Reynolds nu
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easonably well using correlations e
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in the section on blade cooling tha
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mass flow rate (e.g., M ¼ 1 for a
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holes. Cooling hole pattern is an i
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coolant flow with the main stream,
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above equation assumes a constant f
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Figure 15 Definition of film-coolin
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edistribution of the external heat-
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Three-Dimensional Effects The three
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In order to achieve the bulk metal
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coefficient is given by Nud ¼ hd=k
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Where G ¼ 2:24ðw=tÞ 0:1 ðReeÞ
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pressure drop. The 608/458 V-shaped
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Some of the studies have found that
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of the cooling air and the turning
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Figure 20 Impingement geometry defi
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correlated by Nu a d ¼ 0:63ðGd=m
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tangentially to the inner wall, beh
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The effectiveness of a suction surf
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vortex structure. Their studies sho
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Figure 23 Effect of preswirler pres
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component to the cooling air that c
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axial gap. A static pressure variat
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Weight, cost, and complexity constr
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Figure 28 Effectiveness of liner co
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thickness. A problem this poses is
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portion of the hole has been shown
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unacceptable engine performance pen
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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
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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
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design fault in the radial-inflow t
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[27]. In order to avoid manufacturi
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The rotor exit critical velocity is
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The hub-to-tip radius ratio at the
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REFERENCES 1. A. J. Glassman (ed.),
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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
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First Law of Thermodynamics The fir
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the amount of fuel burned and the p
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Figure 7 Rankine cycle temperature-
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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
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calculate the relevant thermodynami
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Figure 14 Steam leakage losses for
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can reveal nozzle and/or blade eros
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Figure 17 Enlarged portion of the M
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Traditionally, pressures have been
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Figure 21 Wetness thermodynamic los
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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
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Figure 30 Typical low-pressure stea
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ductility and poor toughness, since
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‘‘tramp’’ elements to minim
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End Seals End seals or packing glan
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Drains Condensate can form during s
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Figure 32 Steam turbine blade roots
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Figure 34 Cross-section view of thr
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Figure 36 Interblade shroud and Tie
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Where The influence of notch sensit
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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
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Figure 38 Centrifugal stresses on a
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Figure 39 Centrifugal bending stres
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onto the rotating blade. These can
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Vortex shedding from blade trailing
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Figure 42 Torsional coupled vibrati
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Figure 44 Stall flutter of low-pres
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Start-Stop Transients/Overspeeds La
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(4) ellipiticity, such as caused by
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Figure 47 Campbell diagram (frequen
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Furthermore, in practice each manuf
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Figure 49 Modal diameters of a low-
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Figure 51 Three-dimensional computa
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Figure 52 Converging wedge and resu
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value as the operating value of uv/
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Lubrication Supply System Design De
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Figure 56 Steam turbine oil system
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The main oil reservoir is located b
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Although a light oil does provide a
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temperatures are suspected as reaso
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There is no fixed or absolute value
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pivots incorporated in this bearing
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covers and doors. Pipe scale, rust,
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Figure 63 Mechanical hydraulic cont
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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
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the turbine against overspeed. This
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an additional electronic overspeed
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Figure 68 Steam turbine protective
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3. Need for better understanding of
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REFERENCES 1. J. C. Zink, ‘‘Ste
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No. TWDPS-1, The American Society o
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58. A. V. Sarlashkar and T. C. T. L
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81. IEEE Guide for Abnormal Frequen
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Atlanta, GA, Oct. 18-22, 1992, PWR-
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Performance Enhancement Program, he
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of the design process toward achiev
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procedure capable of addressing mul
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to achieve a specific target pressu
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objective was to minimize the downs
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more closely represents the largest
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temperature by forming a thin film
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such as the one described here. For
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k is the thermal conductivity of th
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through finite differences. Mathema
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Figure 4 Comparison of blade cross-
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integration of multiple disciplines
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17. S. S. Talya, ‘‘Multidiscipl
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INTRODUCTION 10 Rotordynamic Consid
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Figure 1 (c) AlliedSignal 331 turbo
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Figure 2 Rotor system displacements
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Figure 3 Elliptic lateral whirl. av
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vibration (either forward or backwa
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Figure 6 The Laval-Jeffcott rotor.
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are 1808 out of phase (i.e., the be
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this graph is quite simple; however
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included on these types of graphs b
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on the shaft is zero. Thus, the ste
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are uðtÞ ¼e zeott uo cos ott þ
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satisfies the inequality O < ot 1
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Figure 16 Laval-Jeffcott rotor tran
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Figure 18 Whirl speed map: Laval-Je
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Figure 20 Laval-Jeffcott rotor: ste
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Figure 22 Typical precessional mode
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Figure 24 Examples of flexible disk
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ackward modes, however, involve con
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Figure 29 Steady unbalance response
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assist in attenuating high vibratio
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properly sizing the damper, a highl
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Figure 31 Gas turbine schematic and
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Flexible Disk If the frequency of a
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motion for each subsegment to form
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Figure 35 Whirl speed map—straddl
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Figure 37 Rotor-bearing-support str
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DESIGN STRATEGIES AND PROCEDURES Ro
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Figure 38 Straddle mounted rotor. (
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Figure 39 Unbalance response: strad
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Figure 40 Double overhung rotor—d
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earing supports are reduced. The th
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and also increases the critical spe
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Examples of structure modes couplin
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REFERENCES 1. D. Childs, Turbomachi
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section is intended to place today
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pressure-fed propellant systems. Hi
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normally be considered a very small
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increase of required suction perfor
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displaced by the F-1 oxidizer pump
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exposure may be subjected to imping
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the exhaust duct. Sized to create s
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excess of 6,000 psi for consumption
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lifetime. With very few exceptions,
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using hydrocarbon fuel combustion p
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can yield noticeable savings in req
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Figure 3 Rocket engine system schem
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Figure 6 Staged combustion system,
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each stage. The term C0 represents
Page 695 and 696:
Figure 10 Some representative turbo
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emembered that the second (and any
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the greatest demands on turbopump p
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momentum exchange between working f
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Figure 13 Arrangement of various tu
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pressure levels. As long as combust
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Figure 14 Approxmate values of pump
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liquid rocket engine systems, and e
Page 711 and 712:
above becomes a factor. This statem
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We can then state (correctly) that,
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Figure 15c Typical 2-D centrifugal
Page 717 and 718:
have seen that the flow rate throug
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somewhat smaller magnitude of vecto
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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
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In addition to shaft seals, shaft b
Page 729 and 730:
should be understood that the optim
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stable operation is assured. In som
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From Eq. (16) an impeller radial ou
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Figure 18 Examples of centrifugal p
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tional to clearance distance) with
Page 739 and 740:
I would like to conclude this secti
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generally result in lower pump hydr
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Figure 15h Cross-section of a typic
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solutions of Eq. (7) for both stage
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Figure 15k H-Q characteristics for
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Figure 15l Typical inducer configur
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camber) is proportionally lower. Th
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Figure 22 Single-stage impulse turb
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the velocity ratio K, but in somewh
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~V and ~n ¼ fluid velocity and con
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Fig. 25. The nature of the flow in
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Although shrouded centrifugal impel
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is a parasitic device, whose flow r
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apidly than does the inducer thrust
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Figure 30 LH2 turbopump rotor mecha
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eplacement of a failed bearing with
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shall see, contemporary rocket engi
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needs of the aircraft gas turbine a
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was increased due to engine upratin
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12 Turbomachinery Performance Testi
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istics. The more accurate the perfo
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Inlet Distortion Most turbomachiner
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Gas Thermodynamic Properties Turbom
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ought to rest isentropically. Total
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include not only the pressure chang
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The circumferential placement of th
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simply arithmetically averaging the
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usually mounted in radial immersion
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Figure 12(b) Radial flow angle prof
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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
Page 819 and 820: INTRODUCTION 13 Automotive Supercha
Page 821 and 822: Figure 2 A Roots-type supercharger
Page 823 and 824: The supercharger was in routine use
Page 825 and 826: Table 1 Superchargers Versus Turboc
Page 827 and 828: 1960s, turbocharging was used by US
Page 829 and 830: Roots Blower The Roots-type blower
Page 831 and 832: speeds. The sound is caused by the
Page 833 and 834: Figure 8b How the Ro-charger operat
Page 835 and 836: The vanes in many designs are preve
Page 837 and 838: Figure 11a Key components of the G-
Page 839 and 840: Figure 11c G-Lader supercharger is
Page 841 and 842: Figure 12b Schematic of centrifugal
Page 843 and 844: Figure 14b Components of the typica
Page 845 and 846: Turbine Design The turbine housing
Page 847 and 848: inertia of the wheel assembly. Mini
Page 849: Figure 18 (a) Turbocharger compress
Page 853 and 854: The overall turbine efficiency incl
Page 855 and 856: adjust the spring force to vary the
Page 857 and 858: Figure 22b Two vanes are used to pr
Page 859 and 860: However, the temperature has to be
Page 861 and 862: air can reduce carbon monoxide and
Page 863 and 864: Figure 25 (a) Schematic of the COMP
Page 865 and 866: this plus the fact that the exhaust
Page 867 and 868: 14 Tesla Turbomachinery Warren Rice
Page 869 and 870: press at the time of the invention
Page 871 and 872: can be made to simplify the equatio
Page 873 and 874: comparison of the results of variou
Page 875 and 876: y composing them of nested cones ra
Page 877 and 878: 26. E. Bakke, ‘‘Theoretical and
Page 879 and 880: 61. M. Piesche, ‘‘Investigation
Page 881 and 882: 15 Hydraulic Turbines V. Dakshina M
Page 883 and 884: Table 1 Variables of Interest in Tu
Page 885 and 886: Figure 1 Variation of impeller shap
Page 887 and 888: Figure 2 Flow and velocity componen
Page 889 and 890: Figure 3 Schematic diagram of Pelto
Page 891 and 892: shown in Fig. 5(see KadambiandPrasa
Page 893 and 894: classified according to the directi
Page 895 and 896: The manufacturers of hydraulic turb
Page 897 and 898: The direction of the relative veloc
Page 899 and 900: Table 3 Variation of Some Quantitie
Page 901 and 902:
denoted by hd. Thus the efficiency
Page 903 and 904:
Figure 14 Draft tube setting. same
Page 905:
REFERENCES 1. J. J. Fritz, Small an
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Handbook of Turbomachinery Second Edition Revised - Ventech!

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