Handbook of Turbomachinery Second Edition Revised - Ventech!

More documents

Recommendations

Info

Figure 7 3-D high pressure turbine design of Kingcombe et al. [26]. Figure 8a Predicted and measured contours of isentropic Mach number for the vane in the turbine of Kingcombe. Copyright © 2003 Marcel Dekker, Inc.
Figure 9 Nusselt number vs. vane surface length. Comparison of predicted and measured vane surface mid-span Nusselt number at design. that this is one of the first reasonably successful fully 3D heat-transfer predictions. THIN-LAYER NAVIER–STOKES ANALYSIS At this point we have examined two approaches for the fluid dynamic solution in the main flow region and the boundary layers. The first was a quasi-3D approach based on potential flow solutions coupled with a 2D boundary-layer code operating along the streamlines at the surface. Second, we looked at a fully 3D main flow solution of the nonviscous Euler equations again with a 2D boundary-layer code following the surface streamlines. An intermediate method that takes into account viscous effects in more detail is known as thin-layer Navier–Stokes analysis, in which the Navier–Stokes (N–S) equations are used in a quasi-3D approach. Here the full Navier–Stokes equations are solved on the blade-to-blade surface, and the solution extends across the passage from wall to wall, eliminating the Copyright © 2003 Marcel Dekker, Inc.
Page 1 and 2:
D E K K E R Handbook of Turbomachin
Page 3 and 4:
MECHANICAL ENGINEERING A Series of
Page 5 and 6:
61 Computer-Aided Simulation in Rai
Page 7 and 8:
127 Designing for Product Sound Qua
Page 9 and 10:
Preface to the Second Edition The o
Page 11 and 12:
Preface to the Second Edition Prefa
Page 13 and 14:
Contributors Nathan G. Adams The Bo
Page 15 and 16:
1 Introduction Earl Logan, Jr.*, an
Page 17 and 18:
HISTORICAL BACKGROUND Earl Logan, J
Page 19 and 20:
MECHANICAL AND THERMAL DESIGN CONSI
Page 21 and 22:
Figure 1 Cross-section showing the
Page 23 and 24:
Figure 2 Turboprop engine, TPE 331-
Page 25 and 26:
Figure 4 Auxiliary power unit, APU1
Page 27 and 28:
Durability. The mechanical and ther
Page 29 and 30:
with time during flight. Such a typ
Page 31 and 32:
experience and existing similar des
Page 33 and 34:
adverse pressure gradient against w
Page 35 and 36:
and its attachments. A substantial
Page 37 and 38:
Figure 9 Typical high-pressure turb
Page 39 and 40:
and the measurement of local heat-t
Page 41 and 42:
due to cyclic operation. In additio
Page 43 and 44:
the steady and transient conditions
Page 45 and 46:
Table 3(a) Steps in a Three-Dimensi
Page 47 and 48:
Figure 16 Schematic Goodman diagram
Page 49 and 50:
occur due to particles of unburned
Page 51 and 52:
pressures at critical points. These
Page 53 and 54:
1. Ceramics are subject to ‘‘in
Page 55 and 56:
with Transient Tests and Surface Co
Page 57 and 58:
Overall engine performance goals tr
Page 59 and 60:
Much of the complexity of turbomach
Page 61 and 62:
End-wall boundary layers can also h
Page 63 and 64:
pressure at the wake centerline. Th
Page 65 and 66:
the same vaneless diffuser and shro
Page 67 and 68:
from internal cooling passages, thr
Page 69 and 70: Further downstream, the wake was ev
Page 71 and 72: to its original position. This unst
Page 73 and 74: cooling film was found to trip the
Page 75 and 76: shroud static pressure and the exit
Page 77 and 78: stage in the design process allows
Page 79 and 80: Flow Physics Modeling Modeling of t
Page 81 and 82: passage to the next, assuming that
Page 83 and 84: The next step in modeling accuracy
Page 85 and 86: tend to be large, due to the necess
Page 87 and 88: Navier-Stokes equations are time-ma
Page 89 and 90: To satisfy these requirements, it i
Page 91 and 92: are discussed by a number of author
Page 93 and 94: source code, and to assign each seg
Page 95 and 96: selected locations in the flow path
Page 97 and 98: of the component designers must be
Page 99 and 100: Trends in Flow Modeling Capabilitie
Page 101 and 102: optimize the flow behavior. The eff
Page 103 and 104: 20. D. Eckardt, ‘‘Flow Field An
Page 105 and 106: 49. K. R. Kirtley, ‘‘An Algebra
Page 107 and 108: INTRODUCTION 3 Turbine Gas-Path Hea
Page 109 and 110: Figure 1 Maximum turbine rotor inle
Page 111 and 112: Figure 2 Intersecting S1 and S2 sur
Page 113 and 114: determination. Nothing in the simpl
Page 115 and 116: e well matched with the engine. The
Page 117 and 118: case different forms of the popular
Page 119: volume will be equal to the accumul
Page 123 and 124: Furthermore, to keep computer time
Page 125 and 126: Figure 12 Comparison of three turbu
Page 127 and 128: and small and cooled and uncooled t
Page 129 and 130: Figure 15 Miniature heat flux gauge
Page 131 and 132: Figure 17 Time resolved heat transf
Page 133 and 134: Figure 19 Surface pressure changes
Page 135 and 136: 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 and 188:
holes. Cooling hole pattern is an i
Page 189 and 190:
coolant flow with the main stream,
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
Page 239 and 240:
Figure 30 Application of PSP for fi
Page 241 and 242:
thermocouple positioned close to th
Page 243 and 244:
spray-painted black (Hallcrest, BB-
Page 245 and 246:
Figure 32 Schematics of a hot casca
Page 247 and 248:
the turbine static temperature (rot
Page 249 and 250:
Figure 33 Experimental rig for inve
Page 251 and 252:
their color when exposed to higher
Page 253 and 254:
margins defined within each discipl
Page 255 and 256:
them. The larger gas-path divergenc
Page 257 and 258:
Figure 36 Blade-cooling selection d
Page 259 and 260:
8. B. Barry, Turbine Blade Cooling:
Page 261 and 262:
40. A. K. Tolpadi and M. E. Crawfor
Page 263 and 264:
73. R. S. Abhari, ‘‘Comparison
Page 265 and 266:
106. J. M. Owen and R. H. Rogers, F
Page 267 and 268:
138. I. Egorov, G. Kretinin, I. Les
Page 269 and 270:
integrity (stress levels) will have
Page 271 and 272:
Figure 1 Instant entropy contours o
Page 273 and 274:
Aerodynamic Interaction (Unsteady L
Page 275 and 276:
Figure 3 Pitchwise time-averaged en
Page 277 and 278:
The above considerations are all fo
Page 279 and 280:
lades, the wavelength of the distur
Page 281 and 282:
forcing and damping, and hence the
Page 283 and 284:
frequency and its higher harmonics
Page 285 and 286:
The two-cell pattern with a relativ
Page 287 and 288:
Figure 9 Typical blade flutter boun
Page 289 and 290:
field is generated to satisfy the t
Page 291 and 292:
Figure 11 Instant static pressure c
Page 293 and 294:
Figure 12 Calculated instantaneous
Page 295 and 296:
Figure 14 Time-space static pressur
Page 297 and 298:
one period Tp (neglecting change of
Page 299 and 300:
It should be noted that the effects
Page 301 and 302:
There are some further points to no
Page 303 and 304:
Figure 17 Flow around an NACA-65 ai
Page 305 and 306:
(11) for a simple case]: Where WA
Page 307 and 308:
Regardless whether loosely coupled
Page 309 and 310:
Several methods have been developed
Page 311 and 312:
significant difference is introduce
Page 313 and 314:
losses, but it may affect to a mini
Page 315 and 316:
when we refine a mesh in an unstead
Page 317 and 318:
8. W. S. Barankiewicz and M. D. Hat
Page 319 and 320:
6 Fundamentals of Compressor Design
Page 321 and 322:
Figure 3 AlliedSignal 331 turboprop
Page 323 and 324:
each of the selected radii. The pro
Page 325 and 326:
components of gas velocity upstream
Page 327 and 328:
Observe that each of the curves for
Page 329 and 330:
The conservation of angular momentu
Page 331 and 332:
allowable static pressure ratio of
Page 333 and 334:
Figure 7 Boundary layers and wakes
Page 335 and 336:
component that is perpendicular to
Page 337 and 338:
Figure 10 (a) Deflection of flow of
Page 339 and 340:
increase in the downstream pressure
Page 341 and 342:
Mach number at a compressor outlet
Page 343 and 344:
Figure 12 Sketch of flow surface an
Page 345 and 346:
useful shapes and orientations of b
Page 347 and 348:
where G and oa are constant along a
Page 349 and 350:
There is a good reason for this sit
Page 351 and 352:
Projected Shape in Meridional Plane
Page 353 and 354:
inherent flow range of the impeller
Page 355 and 356:
compressors. Multistage centrifugal
Page 357 and 358:
turbines. In these designs the high
Page 359 and 360:
Corrections for Streamline Curvatur
Page 361 and 362:
Preparation of Maps Once the losses
Page 363 and 364:
that circumferential gradients meas
Page 365 and 366:
Nastran, which was developed by NAS
Page 367 and 368:
tests. One should take pains to pro
Page 369 and 370:
e predicted in advance. Total press
Page 371 and 372:
Cv Coefficient of heat at constant
Page 373 and 374:
15. S. Lieblein, J. Basic Eng., Tra
Page 375 and 376:
INTRODUCTION 7 Fundamentals of Turb
Page 377 and 378:
Figure 1 Cross sections of generic
Page 379 and 380:
espectively. Radial-inflow turbines
Page 381 and 382:
Figure 4 Typical rotor blade shapes
Page 383 and 384:
Figure 6 The expansion process acro
Page 385 and 386:
the average for the gas flowing thr
Page 387 and 388:
etween the velocity diagram and the
Page 389 and 390:
gas dynamics relation p 00 p ¼ T 0
Page 391 and 392:
Figure 9 Variations in turbine velo
Page 393 and 394:
pressure, inlet losses are usually
Page 395 and 396:
diffuser recovery, defined as Rp ¼
Page 397 and 398:
different turbines easier, dimensio
Page 399 and 400:
where and y ¼ T 0 in TSTD d ¼ p0
Page 401 and 402:
sizing exercises where the details
Page 403 and 404:
where Rth is the Reynolds number ba
Page 405 and 406:
order to determine the overall turb
Page 407 and 408:
The classical approach to satisfyin
Page 409 and 410:
clearance. Since tip clearance repr
Page 411 and 412:
turbine with an effective diffuser,
Page 413 and 414:
atio ðp 0 in =pdisÞ is 3. The sta
Page 415 and 416:
Automation of Calculations and Trad
Page 417 and 418:
and for the rotor Zrotor ¼ ð0:1Þ
Page 419 and 420:
the energy extracted and the rotor
Page 421 and 422:
RADIAL-INFLOW TURBINE SIZING Differ
Page 423 and 424:
interpolations from existing design
Page 425 and 426:
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
Page 433 and 434:
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
Page 439 and 440:
Figure 3 Reciprocating steam engine
Page 441 and 442:
This process began in the 1920s, al
Page 443 and 444:
First Law of Thermodynamics The fir
Page 445 and 446:
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
Page 451 and 452:
Figure 10 Theoretical Rankine cycle
Page 453 and 454:
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
Page 465 and 466:
Figure 21 Wetness thermodynamic los
Page 467 and 468:
Figure 23 Radial steam turbine flow
Page 469 and 470:
Figure 25 Percentage stage reaction
Page 471 and 472:
The power output of the stage can b
Page 473 and 474:
the LP turbines is split into paral
Page 475 and 476:
Turbine Inlet Two stages in particu
Page 477 and 478:
of 20%, which would cause excessive
Page 479 and 480:
Figure 30 Typical low-pressure stea
Page 481 and 482:
ductility and poor toughness, since
Page 483 and 484:
‘‘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
Page 491 and 492:
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
Page 499 and 500:
those made of steel. Note, however,
Page 501 and 502:
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
Page 551 and 552:
Figure 65 Steam turbine electro-hyd
Page 553 and 554:
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
Page 625 and 626:
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. (
Page 655 and 656:
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
Page 779 and 780:
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
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 and 850:
Figure 18 (a) Turbocharger compress
Page 851 and 852:
Theoretically this efficiency is: o
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
show all

Handbook of Turbomachinery Second Edition Revised - Ventech!

Create successful ePaper yourself

Delete template?

Save as template?