Handbook of Turbomachinery Second Edition Revised - Ventech!

More documents

Recommendations

Info

using products of decomposition of hydrogen peroxide (H2O2) as working fluid. Expanding its gas through a pressure ratio of approximately 22, this turbine delivered just under 800 hp at a shaft speed of 4,800 rpm. The most serious limitation suffered by systems of this sort is relatively low-power output due to low specific energy of the turbine working fluid. Despite this comparative limitation, monopropellant drive turbomachinery remains in quite high-volume use in countries other than the United States. Rocket engines employing the gas generator cycle comprise the bulk of the engines being produced in the United States today, or that have been produced in the past. In this cycle, a small combustor is supplied with fuel and oxidizer in parallel with the engine’s main combustion chamber. The resulting products of combustion are fed directly to the turbine inlet manifold. Thus, the turbine inlet pressure is, for practical purposes, set at the turbopump discharge pressure less the pressure losses in the gas generator combustion system. Typical values of inlet pressure for gas generator cycle turbines have ranged from 400 to 1,000 psi. The turbine designer could, of course, reduce the turbine inlet pressure by means of pressure reducing or regulating devices in the gas generator propellant systems, although this is not common practice. The turbine exhaust pressure in gas generator cycle turbines may or may not be dependent on other engine cycle considerations. In the simplest instances, turbine exhaust gases are simply transported to the base plane of the engine by a suitable exhaust duct, where they vent to atmosphere. In these cases, turbine exhaust pressures are only slightly above atmospheric pressure. Such systems also typically include a restricting orifice in the turbine exhaust duct. This orifice, along with the turbine exhaust pressure level, is sized to induce sonic flow through the orifice. This technique ensures that the turbine pressure ratio (and thus turbine power) will not vary with altitude. The other popular method of disposal of gas generator cycle turbine exhaust gas involves transporting the gas to an annular manifold around the divergent section of the engine exhaust nozzle. Here, the gas is injected into the nozzle’s supersonic flow stream. The turbine exhaust is cool relative to the total temperature of the main chamber gas and is used in this instance to provide a boundary layer adjacent to the nozzle wall that is cool enough to negate the requirement for regenerative cooling in the lower portion of the nozzle section. This practice is referred to as dump cooling and has certain advantages. The smaller the fraction of the nozzle length that must be regeneratively cooled, the lower is the discharge pressure requirement of the propellant pump that is delivering the coolant fluid. Since the regenerative cooling process depends on high coolant velocities, the pressure losses across a large nozzle’s coolant circuit can be substantial. Even a relatively small reduction in the regeneratively cooled nozzle length Copyright © 2003 Marcel Dekker, Inc.
can yield noticeable savings in required turbopump power. Locating the turbine exhaust within the engine nozzle sets the turbine exhaust pressure at the level that exists within the nozzle at the plane where the dump coolant injection will occur. The larger the fraction of the nozzle length that is dump-cooled, the further upstream in the nozzle flow the dump coolant will be introduced. Moving the turbine exhaust manifold further upstream exposes the turbine exhaust to progressively higher static pressures. This results in lower available turbine pressure ratios. Whether or not this method of turbine exhaust disposal is to be used depends, of course, on a number of factors. During the engine preliminary design, parametric studies involving turbine pressure ratio, pump discharge pressure, nozzle coolant jacket pressure drop, and others must be performed to assess the desirability of dump cooling. As a general rule, nozzles intended for operation at or near sea level may not benefit substantially from dump cooling, while nozzles optimized for high-altitude operation can benefit greatly. The staged combustion cycle and expander cycle (of which several derivatives have emerged) mandate a somewhat different approach than the gas generator cycle to the issue of setting turbine inlet and outlet pressures. As stated earlier, the turbine inlet pressure in the gas generator cycle is determined by the turbopump discharge pressure that is required to meet the target main combustion chamber pressure. Gas generator propellant flow is then determined by turbine efficiency at the specified pressure ratio. Staged combustion and expander cycles, in contrast, generally use most or all of the flow of one of the propellants for turbine drive. (A prototype engine recently built worked on a variant of the expander cycle known as the dual expander. In this case, both fuel and oxidizer were used for cooling of different portions of the combustion chamber and nozzle. Separate turbines were employed for each pump, and each used its own pumped fluid for turbine drive.) The pump discharge pressure is then determined from the turbine pressure ratio needed to meet the turbine work requirement. If the reader detects an element of circular logic here, that detection is to be applauded! As can be seen from the schematic representations in Figs. 1–5, both staged combustion and expander cycles set the turbine exhaust pressure from the required pressure in the main combustion chamber injector’s fuel manifold. The turbine inlet pressure is then set by the turbine work required by the propellant pump(s) being driven. At this point, the efficiencies of both turbine(s) and pump(s) come into play. Since pump discharge pressure and turbine inlet pressure must be identical (neglecting losses in between these two points), this pressure must be determined iteratively. A representative method could involve aset of parametric computations as shown in Figs. 6, 7, and 8. Shown is afamily of curves of turbine work generated and pump work input required versus pump discharge pressure. As can be seen, lower 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 and 120:
volume will be equal to the accumul
Page 121 and 122:
Figure 9 Nusselt number vs. vane su
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: using hydrocarbon fuel combustion p
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?