dynamic and static analysis of turbogenerator foundation

8/9/2019 Dynamic and static analysis of turbogenerator foundation

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DYNAMIC & STATIC

ANALYSIS

Turbo Generator Foundation

Rev. 1

GERB Engineering GmbHRuhrallee 311, D-45136 EssenPhone: +49-(0)201-26604-20Fax: +49-(0)201-26604-50Email: [email protected]

Kunde / Client:

BUSHAN STEEL LTD.

Datum / Date:22.06.2011

Projekt / Job:

MERAMANDALI 165 MW STG - UNIT 4Vibration Isolation of a Turbo Generator Set

Aufsteller / Author:

M. GeisDr.-Ing.

Projekt-Nr. / Job-No.:

E-58144-1-4 Rev. 1


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BUSHAN STEEL LTD. Page IMERAMANDALI 165 MW STG - UNIT 4

Vibration Isolation of a Turbo Generator Set Rev. 1

GERB Engineering GmbHRuhrallee 311, D - 45136 Essen / Germany,+49-201-2660420

Scope and Subject of the Report: Dynamic and Structural Analysis for a spring supportedTurbine Generator Foundation

Document number : E-58144-1-4Revision number : 1Revised pages : IIII, 2, 3, 4, 8 - 11, 1522, 25, 27, 28, 4062, 1003 - 1054Date : 22.06.2011Number of pages : I - III, 1 -62 plus Appendix consisting of pages 10011054

Author : M. GeisDr.-Ing. ___________________________sign.

Approved : S. GutbergerDipl.-Ing. ___________________________sign.

Client : BUSHAN STEEL LTD.Order number : -Order date : -


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BUSHAN STEEL LTD. Page IIMERAMANDALI 165 MW STG - UNIT 4



CONTENTS

Page

1 S U M M A R Y ...................................................................................................................... 11.1 General ............................................................................................................................. 11.2 Building Materials .............................................................................................................. 11.3

Reference Documents ...................................................................................................... 2

1.4 Main System Data ............................................................................................................. 21.5

Machine Data .................................................................................................................... 2

1.6 Vibration Isolation System ................................................................................................. 31.7

Discussion of Dynamic Characteristic ............................................................................... 3

1.8 Theoretical Amplitudes ...................................................................................................... 41.9 Seismic Loads ................................................................................................................... 51.10

Literature ........................................................................................................................... 6

1.11

Software ............................................................................................................................ 7

1.12 Calculation Models ............................................................................................................ 71.13

Determination of Cross Section Properties ...................................................................... 11

1.14 Input Data ....................................................................................................................... 121.14.1 Input of the Calculation Model ......................................................................................... 121.14.2

Input for dynamic analysis ............................................................................................... 13

1.14.3 Input for static analysis .................................................................................................... 13

2 D Y N A M I C A N A L Y S I S .......................................................................................... 142.1 Foundation and Machine Masses .................................................................................... 142.2 Results of Dynamic Analysis ........................................................................................... 152.2.1 General ........................................................................................................................... 15

2.2.2

Comments on the Results ............................................................................................... 15

2.2.3

Plot of the Mode Shapes ................................................................................................. 16

2.3 Determination of Vibrational Amplitudes .......................................................................... 232.3.1 Excitation by Unbalanced Forces .................................................................................... 232.3.2

Superposition of Theoretical Amplitudes ......................................................................... 24

2.3.3 Frequency Response of Amplitudes ................................................................................ 242.4 Dynamic Element Loads due to Unbalance ..................................................................... 26

3 S T A T I C A N A L Y S I S ............................................................................................... 273.1 General ........................................................................................................................... 273.2

Compilation of Load Cases ............................................................................................. 27

3.3 Description of the Single Load Cases ............................................................................. 28

3.3.1

Load Case 1 - Dead Load Foundation............................................................................. 28

3.3.2 Load Case 2Machine Loads ........................................................................................ 293.3.3 Load Case 3Condenser Loads .................................................................................... 303.3.4

Load Case 4Live Load ................................................................................................ 31

3.3.5 Load Case 5Power Torque ......................................................................................... 323.3.6 Load Case 6Thermal Forces X ................................................................................... 333.3.7

Load Case 7Thermal Forces Y.................................................................................... 34

3.3.8 Load Case 8Thermal Forces Z .................................................................................... 353.3.9

Load case 9Pipe Forces X .......................................................................................... 36

3.3.10 Load case 10Pipe Forces Y ........................................................................................ 373.3.11 Load case 11Pipe Forces Z ........................................................................................ 383.3.12

Load case 12 - Erection load ........................................................................................... 39

3.3.13

Load case 13 - Erection load ........................................................................................... 40

3.3.14 Load case 14 - Loss of blade Y ....................................................................................... 41 3.3.15

Load case 15 - Loss of blade Z ....................................................................................... 42


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BUSHAN STEEL LTD. Page IIIMERAMANDALI 165 MW STG - UNIT 4



3.3.16

Load case 16 - Short circuit () ....................................................................................... 43

3.3.17 Load case 17 - Seismic load X ........................................................................................ 443.3.18 Load case 18 - Seismic load Y ........................................................................................ 453.3.19

Load case 19 - Seismic load Z ........................................................................................ 46

3.3.20 Load Case 20 to 31Seismic Combinations .................................................................. 473.3.21

Load Case 32 to 37Dynamic Loads at Malfunctional States ........................................ 47

3.4 Superposition of Load Cases .......................................................................................... 483.5 Design Forces and Moments .......................................................................................... 503.5.1

Design Moments due to Operational Combinations ........................................................ 51

3.5.2 Design Moments due to Erection Combinations .............................................................. 533.5.3 Design Moments due to Emergency Combinations ......................................................... 553.6 Design of Reinforcement ................................................................................................. 573.6.1 Building materials ............................................................................................................ 573.6.2

Calculation method ......................................................................................................... 57

3.6.3 Required Reinforcement ................................................................................................. 583.6.4 Chosen reinforcement ..................................................................................................... 61

4

S P R I NG F O R C E S .................................................................................................... 62

4.1 Spring Forces and Deflections ........................................................................................ 624.2

Loads on Substructure .................................................................................................... 62

5 A P P E N D I X ............................................................................................................... 10015.1 Data sheets of spring units .......................................................................................... 10015.2

Files of Dynamic Analysis ........................................................................................... 1003

5.3 Files of Dynamic Analysis ........................................................................................... 10035.3.1

Input File of Modal Extraction ...................................................................................... 1003

5.3.2 Results of Modal Extraction Analysis ........................................................................... 10395.3.3 Input Files of Forced Vibration Analysis ...................................................................... 10405.4

Files of Static Analysis ................................................................................................ 1042

5.4.1

Input File of Static Calculation ..................................................................................... 1042

5.4.2 Support Reactions for Single Load Cases ................................................................... 1051


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BUSHAN STEEL LTD. Page 1MERAMANDALI 165 MW STG - UNIT 4



1 S U M M A R Y

1.1 General

The present analysis deals with the design of a vibration controlled reinforced concrete foundationsupporting a steam turbine with generator.

The SUMMARY (1stpart) gives general information and compiles and comments on all relevant

project data including the most important results from the dynamic calculation. References aremade to the corresponding clauses of the calculation where details are shown.

The 2nd

part represents the DYNAMIC ANALYSIS giving evidence about the dynamic behaviour ofthe structure. Eigenfrequencies are calculated as well as forced vibrations are determined due tounbalance at operating stage. Unbalance loads are defined to be used within the structuralanalysis.

The 3rd

part covers the STATIC ANALYSIS considering all relevant load cases. The reinforcementdesign follows the regulations of DIN 1045-1 and DIN 4024 allowing for the below mentionedconcrete and steel qualities. Support reactions and spring deflections due to permanent loads areshown.

Finally, as the substructure below the spring elements is not subject to this paper, design loadsare given to be used by the design engineer in charge of the substructure.

The analysis of the theoretical model is performed on the assumption of a system dynamicallydecoupled from the adjacent structure. Accordingly the spring elements are expected to be placed

on a relative stiff substructure, i. e. the stiffness of the supporting beams shall be at least 10 timesthe stiffness of the spring system (comparison of static deflections) acc. to DIN 4024.

Input and output files of the computational calculation are summarized in the appendix.

1.2 Building Materials

Concrete: Grade (IS 456 - 2000) M 35Compressive strength fck= 35 N/mmStatic modulus of elasticity Ec= 29580 MN/mDynamic modulus of elasticity Ec,dyn= 33700 - 39600 MN/m

Dynamic modulus of elasticity Ec,dyn= 36500 MN/m (mean value)Density of reinforced concrete = 25 kN/mPoissons ratio = 0.20

Reinforcing Steel: Grade (IS 1786 - 1985) Fe 415Yield strength fyk= 415 MN/mModulus of elasticity 210000 MN/m

The design was performed according to DIN 1045-1 and DIN 4024, chapter 6, April 1988.


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1.3 Reference Documents

SIEMENS:dwg. n 1CSD420886 sh. 1 - 6 foundation outline drawing

dwg. n 1CYJ257586G45 sh. 1 - 2 trenches, cutouts and detailsdoc. n 1CSD420885 foundation loads and design requirements

GERB Engineering GmbH:dwg. n E-58144-2-0 et. seq. formwork drawingsdwg. n E-58144-6-0 et. seq. reinforcement drawings

1.4 Main System Data

Total length: L = 25.40 m

Total width: B = 10.60 m

Machine weight: Gm = 4731 kN

Concrete weight: Gf 12286 kNRatio: Gf/ Gm = 2.60

Total spring supported weight: Gt 17017 kNVertical mode: ne = 4.2 HzRelevant operation frequencies: fm = 50 HzMean spring deflection due to dead load: u = 14.6 mm

1.5 Machine Data

Turbinestatic weight (incl. rotating weight): G = 1658 kNrotating weight: L = 290 kNrotating speed: fm = 3000 min

-1

Generatorstatic weight (incl. rotating weight): G = 2502 kNrotating weight: L1 = 460 kNrotating speed: fm = 3000 min

-1

Condenserstatic weight (on table top): G = 571 kN

Total machine weight: Gm = 4731 kN


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1.6 Vibration Isolation System

The top deck is supported by spring elements consisting of helical steel springs.Manufacturer: GERB Vibration Control Systems Pvt. Ltd.

For detailed information about spring elements refer to data sheets at the Appendix.

Spring element arrangement

column kv kh Kv Kh

kN/mm kN/mm kN/mm kN/mm

A1 6 17.23 12.30 103.38 73.80

B1 12 17.23 12.30 206.76 147.60

C1 12 17.23 12.30 206.76 147.60

D1 4 17.23 12.30 68.92 49.20

A2 6 17.23 12.30 103.38 73.80

B2 12 17.23 12.30 206.76 147.60

C2 12 17.23 12.30 206.76 147.60

D2 4 17.23 12.30 68.92 49.20

68 1171.64 836.40

GP-8.8-2513/22

GP-8.8-2513/22

GPV-8.8-2513/22

number

n

spring rate total spring rate

spring element type

total spring rate

GPV-8.8-2513/22

GP-8.8-2513/22

GP-8.8-2513/22

GPV-8.8-2513/22

GPV-8.8-2513/22

Total spring rate Kv = 1171.6 kN/mmKh = 836.4 kN/mm

For loadings on sub-structure refer to clause (4.2)of this paper.

1.7 Discussion of Dynamic Characteristic

Modes 1 to 6 represent the rigid body natural frequencies. Higher modes depend on the elasticityof the structure only. They are virtually decoupled from the rigid body modes.

Evaluation of the results in respect of DIN 4024, 5.3.2:

1. f1= 3.2 Hz 0.80 fm = 0.80 50.0 = 40.0 Hzf6= 6.2 Hz 0.80 fm = 0.80 50.0 = 40.0 Hz

2. a) f14= 46.3 Hz 0.90 fm = 0.90 50.0 = 45.0 Hzf15= 47.0 Hz 0.90 fm = 0.90 50.0 = 45.0 Hz

1.10 fm = 1.10 50.0 = 55.0 Hz

The requirements of DIN 4024 are not fulfilled in regard of the natural frequencies.

For this reason DIN 4024 prescribes a more precise assessment of vibration behaviour bydetermination of dynamic amplitudes (ref. to clause (1.8)).


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1.8 Theoretical Amplitudes

Theoretical amplitudes are calculated due to unbalance caused by the machine at normaloperation. The unbalanced forces are calculated acc. to DIN ISO 1940. Vibrational amplitudes

from the single-force excitation at the bearing points are determined by using the SRSS-method(for details refer to clause (2.3)).

Acc. to ISO 10816-2 the limiting value of the effective vibration velocity for a operating speed of3000 min

-1is recommended as :

veff= 3.8 mm/s (Zone A/B)

For a balance quality grade of G6.3 the maximum velocities at the operating speed

(f = 50 Hz 5%) have been calculated to

max veff= 1.2 mm/s < 3.8 mm/s at 47.5 Hz

The corresponding half-peak amplitudes result to:

s = veff* 2 / (2**fm) = 5 m

The requirements for the limitation of vibration velocities and amplitudes recommended in ISO10816-2 are fulfilled.


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1.9 Seismic Loads

Site of MERAMANDALI is located in seismic zone III as defined in the Indian Standard: 1893-2002.

The design value of horizontal seismic coefficient Ahshould be computed as given by the followingexpression:

Ah = Z I Sa/ ( 2 R g ) * = 0.16 1.75 2.50 / 2 * 0.80 = 0.280

Note:The ratio I / R shall not be greater than 1.0! It follows:

Ah = 0.16 1.0 2.50 / 2 * 0.80 = 0.160 < 0.200

where

Z = 0.16 (seismic zone factor depending upon the seismic zone acc. to table 2)I = 1.75 (importance factor depending upon the category of structure

acc. to table 2 & table 5 of IS: 1893 - part 4)Sa / g = 2.50 (spectral acceleration coefficient as read from fig. 2 (response spectra) for

rock and soil sites for 5% damping)R = 1.0 (response reduction factor for building systems acc. to table 7; for spring

supported systems R = 1.0)

= 0.80 (correction factor for 10% damping)

For any structure with natural period T 0.10 sec., the value of Ahwill not be taken less than Z/2.

According to the Indian standard the vertical seismic coefficient should be taken as two-thirds ofthe horizontal value.

In the present static analysis the seismic loads are considered in a quasi-static way by using a

horizontal acceleration factor of 0.200g as well as a vertical acceleration factor of 0.133g !

Note:

For loadings on substructure it is allowed to set the response reduction factor R = 3.0 (acc. to

table 7 of IS 1893-2002). As a result the design value of horizontal seismic coefficient Ahamountsto 0.093. Design loads at top of plinth in horizontal direction should be taken as 9.3% of thepermanent vertical load.


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1.11 Software

The Dynamic and Structural Analysis of the foundation is performed by the program system'STARDYNE' from Bentley Systems Inc. based on the finite-element-method.

To idealize the structure plate elements with five d.o.f. per node are used.

The calculation model is created using 'FEMAP', a finite-element modelling and postprocessingsystem by Siemens PLM Software GmbH.

The determination of the eigenvalues and eigenvectors in the Dynamic Analysis is made using the'LANCZOS Modal Extraction'. The LANCZOS procedure was first described by C. Lanczos (1950)with error analysis added by J. Wilkinson (1965). It was successfully demonstrated in large finiteelement programs by I. Ojalvo and M. Newman (1967 - 1970). The description of the method canbe found in NASA document CR-2731 (1976).

The nodes of the structural model are determined by supports, loading points and cross sectioncuts.

On the next pages the numbering of nodes and elements of the analysis model is shown.Furthermore the geometry is controlled by graphical plots.

Software vendor:

1.12 Calculation Models

The Finite-Element-Model consists of the top deck and the spring elements. The machines arerepresented by single masses which are connected to the plate by rigid bars.

The global x-axis is parallel to the rotor axis, the z-axis is the vertical axis.

The model is shown by plots on the following pages.


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Element Thickness

XY

Z

V2

C1

G3

Calculation Model

XY

Z

V2

C1


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Calculation Model without machines

XY

Z

V2

C1

G1

Node Numbers

X

Y

Z

1 2 3 4 5 6 7 8 9 10 11 12 13 1415 16 17 18 192021 2223 24 25 26 27282930 31 32 33 34 35 3637 38 39 404142 43 4445 46 47 48 49 50 51 52

53 54555657 58 59 60 61 62 6364 65 66 676869 70 7172 73 7475 76 77 78 7980 81 82 83 84 85 86 87 8889 90 91 92 939495 9697 98 99 100101102103104

105106107108109110111112113114115 116 117118119 120 121122123124125126127 128129130131132133134135136137138139140141142 143144145 146147 148149 150151 152153154155156157158159160161162163164165 166 167168169 170 171172173174175176177178179

180181182 183184185186187188 189 190191192193 194195196197

198199 200201202203204205206207208209210211 212213214215216217218219 220221222 223224

225226 227228229230231232233234235236237238239 240

241242 243244245246 247 248249250251252253 254255256257258259260261 262263264 265266 267268 269270271272273 274275276277278279

280281

282

283

284

285286287288 289290291292293294295 296297298299300301 302 303304 305306307308309310311312 313314315316317 318319

320321322 323324325326327328

329

330331 332 333334 335336

337

338339 340 341342343344345 346347348349350351352353354355356357358359 360361362363 364365366367 368369370371 372373374 375376 377378379380381382383384

385386

387

388

389

390391392393 394395396397398399400401402403404405406 407408409

410 411412 413414 415416

417418419 420 421 422423424425426427428429430431432433 434435436437438 439440441442443 444445446 447448 449450 451452453454455

456457458 459460461462 463464465466467 468469470 471472 473474 475476477478479 480 481482483484485486

487488489 490491492493494 495496497498499 500501502 503504 505506 507508509510511 512513514515516517518519520521522 523 524 525

526527528529530 531532533534 535

536537538 539540541542543544545546547 548549550551552553554555

556557558 559560561562 563564565566 567568569 570571 572573 574575576577578579580581582583584585 586587588589590591592593594595596 597598599 600

601602603 604605606607608609 610611 612 613614 615616 617618 619620621622623624 625626627628629630 631632633634635636637638639640641642643644 645646647648649650651652653654655656657658 659 660661 662663664665666667 668669670671672673674675676677678679680681682 683 684 685

686687688689690 691692693694695696697698699700701702703704705706 707708 709 710 711712713714715716717718719720721 722723724725726727728729730 731 732733734 735 736737738 739740741742743744 745746747748749750751752753754755756757758759760 761762 763 764 765766767768769770771772773774775 776777778779780781782

783784785786787 788789790791792793794795796797798799800801802803 804805 806807 808809810811812813814815816817818 819820821822823824825826827 828 829830831 832 833834

835836837838839 840841842843844845846847848849850851852853854855 856857 858 859 860861862863864865866867868869870871872 873 874875876 877 878879880881882883884885886

887888889890891 892893894895896897898899900901902903904905906907 908909 910 911 912913914915916917918919920921922923924 925 926927928 929 930931932933934935936937938

939940941942943 944945946947948949950951952953954955956957958959 960961 962 963 964965966967968969970971972973974975976 977 978979980 981 982983984985986987988989990

991992993994995996

997

998

9991000

1001

1002

1003

1101

1102

1103

1104

1105

1106

1107

1108

1109

1110

1111

1112

1113

1114

1115

1116

1117

1201

1202

1203

1204

1205

1206

1207

1208

1209

1210

1211

1212

1213

1214

1215

1216

12173022 3025 3028 3031 3034 3037

V5

C1

G3


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Node Numbers (selected nodes)

X

Y

Z

1101

1102

1103

1104

1105

1106

1107

1108

1109

1110

1111

1112

1113

1114

1115

1116

1117

1201

1202

1203

1204

1205

1206

1207

1208

1209

1210

1211

1212

1213

1214

1215

1216

12173001 3002 3003 30043005 3006

4001 4002 4003 4004

4005 4006 4007 4008

V5

C1

G4

Element Numbers

X

Y

Z

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 1920 21 22 23 24 25 26272829 30 31 32 33 34 35 36 37 38 39 4041 42 43 44 45 46 47 48 49 50 51

52 53545556 57 58 59 60 61 62 63 64 65 66 6768 69 70 71 72 73 7475 76 77 78 79 80 8182 83 84 85 86 87 88 89 90 91 92 939495 96 97 98 99100101102103104105106107108109110111112113114 115116117118119120121122123124125126 127128129130131

132133134135136137138139140141142143144145146147 148149 150151152153154

155156 157158159160161162163164165166167168169170171172 173174175176177178 179180181182 183 184185186187188 189

190191192 193194195196197198199 200201202203204 205 206207208209210 211212213214215216217218219 220221222223224225

226227228229230 231232233234235236237 238239240241242243 244245246247248 249250251252253

254 255256257258 259260261262263264265 266267268269270271 272273274 275276277278279280 281 282283284285286287

288289290 291292293294295296297298299 300301302303304305306307308309310 311312313314

315316317318319320321

322 323324325326 327328329 330331332333334335336337338

339340341342343344345346347348349350351

352353354355356357358359360361362363364365 366367368369370371372373 374375376377 378379380381

382383384385386387388389390391 392393394395 396397398399400 401402403404405 406 407408409410411

412413414 415416417418 419420421422423424425426427 428 429430431432433434 435436437438439440441442443444 445446447448 449450451452453454455456457458459460461462463464 465466467468469470471472473474 475476477478 479480481482483484485 486487488 489 490491492493494495496497498499500501

502503504505506507508

509510511 512513514515 516517518519520521522523524525 526 527528529530531532533534535536537538 539540541542543544545546547548549550 551

552553554555556557558559560561562563 564565566567568569570571572573574 575 576577578579580581 582583584585586 587588589590591592593

594595596597 598599600601602603604605606607608609610611612 613614 615 616 617618619620621622 623624625626627628629630631632633634635 636

637638639640641 642643644645646647648649650651652653654655656 657658659 660 661662663664665666667668669670671672 673674675676677678679680681 682683684685686687

688689690 691692693694695696697698699700701702 703704705706707708709710711712713714715716717 718719720 721 722723724725726727728729730731732 733734735736737738

739740741742743 744745746747748749750751752753754755756757758 759760761 762 763764765766767768769770771772773774 775776777778779780781782783 784785786787788789

790791792793794 795796797798799800801802803804805806807808809 810811812 813 814815816817818819820821822823824825826827 828829830831 832833834835836837838839840

841842843844845 846847848849850851852853854855856857858859860 861862863 864 865866867868869870871872873874875876877878879880881882883884885886887888889890891

892893894895896897898

899900901902903904905

906

907

908

909910

911

912

913

V5

C1

G3


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1.14 Input Data

In the Appendix the input decks for the modal extraction and the static analysis are printed. For abetter interpretation the single input cards are described below. The printed figures just give an

example and do not have any relationship to the present project.

1.14.1 Input of the Calculation Model

a) STARTCardg [m/s2]

START 10.

b) MATLG - Card (material parameters)

Nr. Descript. E [kN/m] Poisson [kN/m] T [K-1] DampingMATLG, 1, Concrete 30000000., 0.2, 25., 1.0E-5 0.02

c) NODE - Card (nodal coordinates)no. x1 [m] x2 [m] x3 [m]

NODE, 65, 1.925, 1.65, 0.

d) RESTG - Card (nodal restraint table)node no. T1 T2 T3 R1 R2 R3

RESTG 1 1, 2, 3, 4, 5, 6

e) WGHT - Card (nodal weights)node no. Wx1 [kN] Wx2 [kN] Wx3 [kN]

WGHT, 27, 128., 128., 128.

f) BEAMG - Card (beam element topology)

no. node A node B orient. mat. prop. releases betaBEAMG, 29, 50, 49, 9999 2 7 000000 0

g) BPROP1 - Card (beam properties)no. A [m2] IT [m4] Iy [m4] Iz [m4] shear factors

BPROP1 1 2.2475 0.5644 0.3938 0.45 0., 0.

h) BPROP2 - Card (cross section properties)no. H2 [m] H3 [m]

BPROP2 1 2.2475 0.5644

i) BPROP4 - Card (beam offsets)prop. no.XOFFA [m], YOFFA [m]ZOFFA [m]XOFFB [m] YOFFB [m] ZOFFB

BPROP4 1 0., 0., 0., 0., 0.775, 0.

j) QUADS - Card (plate elements)FROM QPLT, TO QPLT, FROM JA, INCR JB, TO JB, INCR JB, FROM JC, INCR JC,FROM JD, INCR JD, MATLG NO, TYPE, T [m], AXIS ANGLE, INTEG ORDERQUADS, 69,, 115,, 138,, 139,, 116, 1, 1, 1.45,

k) MADDEL - Card (matrix addition table)NO, JA, JB, JC, IMOUT, MAXSIZE

MADDEL, 690, 519, 736, 1

l) MADDXINC - Card (springs)RN, CN, RDOF, CDOF, INCRN, INCCN, RNMAX, CNMAX, Dks [kN/m]

MADDXINC, 5, 5, 3, 3, 1, 1, 6, 6, 30270.0


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1.14.2 Input for dynamic analysis

a) DYNAMIC - Card (Lanczos-analysis control entry)

nout isave ieropt nlowm maxcps shiftpDYNAMIC 0, 0, 0, 40, 0., 0.

1.14.3 Input for static analysis

a) STATIC - card (static analysis control entry)NOUT ITAPE ISAVE IEROPT

STATIC, 1, 0, 0, 0,

b) ACCEL - card (gravitational constants)Vx1 Vx2 Vx3 CGx1 CGx2 CGx3

ACCEL, 0., 0., 9.81, 0., 0., 0.,

c) CONC - card (nodal forces)FROM F1 [kN] F2 [kN] F3 [kN]M1 [kNm]M2 [kNm] M3 [kNm]

CONC, 45, 100., 0., 100., 0., 0., 0.,

d) CONCG - card (nofal force generator)FROM TO INCRE F1 [kN] F2 [kN] F3 [kN] M1 [kNm]M2 [kNm] M3 [kNm]

CONCG, 45, 50, 1, 100., 0., 100., 0., 0., 0.,

e) BMTEMPG - card (beam temperature generator)FROM TO INCRE T [K]

BMTEMPG, 2, 5, 1, 10.0,

f) BMTEMP - card (beam temperature)FROM TO INCRE +T2 [K] -T2 [K] +T3 [K] -T3 [K]

BMTEMP, 2, 5, 1, 10.0, -10.0, 0., 0.,

g) BMLOAD - card (beam loads in global coordinates)FROM TO INCRE ITYPEpx1 [kN/m]px2 [kN/m]px2 [kN/m]

BMLOAD, 2, 5, 1, GL, -10.0, 0., 0.,

h) BMLOAD - card (beam loads in local coordinates)FROM TO INCRE ITYPEpA [kN/m] xpA [-] pB [kN/m] xpB [-]

BMLOAD, 2, 5, 1, D2, -10.0, 0.0, -10.0, 1.0

i) QPRSN - card (area loads)FROM TO INCRE PJA PJB PJC PJD

QPRSN, 2, 5, 1, -5.0, -5.0, -5.0, -5.0


18/120




2 D Y N A M I C A N A L Y S I S

2.1 Foundation and Machine Masses

The mass of the foundation is automatically calculated by 'STARDYNE' taking cross section area,beam element length or plate element area, plate thickness respectively and specific mass ofmaterial into account. The top concrete is considered with its nonstructural mass only, which iscontrolled by the specific mass of the corresponding material group.

b) machine masses

The machine masses are applied as given by the machine manufacturer. The single machinemasses are distributed on nodal points of the calculation model as follows:

generator 3001 31.30




turbine 3003 62.84

turbine 3004 102.96

exciter 1115 6.30

exciter 1116 6.30condenser 1203 4.76

condenser 1204 4.76

condenser 1205 4.76

condenser 1206 4.76

condenser 1207 4.76

condenser 1208 4.76

condenser 1209 4.76

condenser 1210 4.76

condenser 1211 4.76

condenser 1212 4.76

condenser 1213 4.76

condenser 1214 4.76

total = 473.12

mass [t]nodesmachine


19/120


20/120




2.2.3 Plot of the Mode Shapes

The mode shapes of the most relevant natural frequencies are shown by plots on the following

pages.

XY

Z

V2

C1

Output Set: Mode 1 3.21662 Hz

Deformed(1.): Total Translation

XY

Z

V2

C1


Deformed(1.107): Total Translation


21/120




XY

Z

V2

C1



XYZ

V2

C1




22/120




XY

Z

V2

C1



XY

Z

V2

C1




23/120




XY

Z

V2

C1



XY

Z

V2

C1




24/120




XY

Z

V2

C1



XY

Z

V2

C1




25/120




XY

Z

V2

C1



XY

Z

V2

C1




26/120




XY

Z

V2

C1



XY

Z

V2

C1




27/120




2.3 Determination of Vibrational Amplitudes

Theoretical amplitudes are determined due to unbalance caused by the machine at normaloperating condition.

The amplitudes are determined using the steady-state technique.

2.3.1 Excitation by Unbalanced Forces

Balance quality grade according to manufacturer and DIN ISO 1940, table 1:

turbine and generator G2.5 eper= 2.5 mm/s

Balance quality grade for calculation according to DIN 4024:

turbine and generator G6.3 eper= 6.3 mm/s

According to DIN ISO 1940 the unbalanced forces are calculated as follows:

Uper= eper2 fmL / g (permissible residual unbalance)

where: L (rotating weight)fm (rotational speed)

= m= 2fm (angular frequency)g 10 m/s (gravitational constant)

Distribution of unbalanced forces:

e* fm L U

[mm/s] [Hz] [kN] [kN]

generator 3001 6.3 50 230 46

generator 3002 6.3 50 230 46

turbine 3003 6.3 50 145 29

turbine 3004 6.3 50 145 29

nodemachine

If eigenvalues are located within a range of 5% of the operating frequencies, acc. to DIN 4024forced vibrations have to be calculated in resonance for the both adjacent natural frequencies.


28/120




2.3.2 Superposition of Theoretical Amplitudes

Amplitudes are determined for the following nodal points:

bearing 1 to 4: nodal points 3001 to 3004

The vibrational amplitudes at bearing points from single-force excitation are determined by usingthe SRSS-method:

2

ni,

2

i,2

2

i,1eff,i A......AA=A

with Ai,k = Amplitude at bearing point i from excitation with the force kk = 1, 2, 3 ... n

2.3.3 Frequency Response of Amplitudes

The excitation at the different bearing points from 40 Hz to 60 Hz in steps of 0.10 Hz results in thefrequency responses of amplitudes at the above mentioned nodal points.

The constant unbalance force between 40 Hz and 60 Hz is calculated as follows:

Uper(f) = Uper(fm)= eper2fm L / g

Unbalanced Forces

0%

50%

100%

20 30 40 50 60 70 80

f [Hz]

U(f)/Uperm

The superposition is performed in the same way as described in section (2.3.2).

The maximum r.m.s. velocity at operational speed (f = 50 Hz 5%) has been calculated to

max veff = 0.9 mm/s < 3.8 mm/s at 47.5 Hz

For comments on the results refer to clause (1.8).

The plot of the resulting frequency responses is presented below.


29/120




SRSS-superposition of the vibration velocity in the range of 40 to 60 Hz

0.0000

0.0010

0.0020

0.0030

0.0040

0.0050

0.0060

40 45 50 55 60

r.m.s.velocityveff[m/s]

frequency f [Hz]

Frequency Response (SRSS)

3001 - V2 eff. 3001 - V3 eff.

3002 - V2 eff. 3002 - V3 eff.

3003 - V2 eff. 3003 - V3 eff.

3004 - V2 eff. 3004 - V3 eff.

zone A/B


30/120




2.4 Dynamic Element Loads due to Unbalance

The dynamic forces are taken into account by use of the natural mode method acc. to DIN 4024,part 1, sect. 5.4.3 under consideration of the manufacturers design recommendations.

Internal forces are calculated for a steady-state excitation of those natural modes which are in a

range of the operating speed fm10%, i. e. between 45 Hz and 55 Hz.

The maximum vibrational amplitudes at malfunctioning states can be estimated to be less than thesix fold half-peak amplitudes at normal operation.

max veff= 6 * 3.8 mm/s = 22.8 mm/s

max s = max veff* 2 / (2 f) = 22.8 mm/s * 2 / (314/s) = 102 m 0.10 mm

The internal forces and moments due to dynamic excitation therefore are calculated from the

natural mode shapes, which are scaled to a maximum displacement of 100 m.


31/120




3 S T A T I C A N A L Y S I S

3.1 General

The structural analysis of the foundation is performed on the following pages.The calculation model is identical to that of the dynamical analysis.

3.2 Compilation of Load Cases

The following load cases will be considered:

1

2

3

4

5

6

7

8

9

10

11

12

1314

15

16

17

18

19

20

21

22

23

24

25

26

27

28

29

30

31

32 dynamic loads mode 12




36

37

load case description

loss of blade (+/-Y)

dead load

machine load

live load 5 kN/m

operational torque

thermal forces X

erection load

seismic X + 0.3 Y + 0.3 Z

seismic X + 0.3 Y - 0.3 Z

seismic X - 0.3 Y + 0.3 Z

seismic X - 0.3 Y - 0.3 Z

seismic Y + 0.3 X + 0.3 Z

horizontal pipe forces (+/-Y)

seismic load +/-Y

seismic load +/-Z

short circuit

loss of blade (+/-Z)

erection load

seismic load +/-X

seismic Z + 0.3 X + 0.3 Y

dynamic loads mode 16


seismic Z + 0.3 X - 0.3 Y

seismic Z - 0.3 X + 0.3 Y

seismic Z - 0.3 X - 0.3 Y

horizontal pipe forces (+/-X)

condenser load

thermal forces Y

thermal forces Z

vertical pipe forces (+/-Z)

seismic Y + 0.3 X - 0.3 Z

seismic Y - 0.3 X + 0.3 Z

seismic Y - 0.3 X - 0.3 Z

Load cases 1 to 11 represent operating conditions and load cases 12 and 13 consider erectioncondition as well as load cases 14 to 37 emergency situations.


32/120




3.3 Description of the Single Load Cases

3.3.1 Load Case 1 - Dead Load Foundation

The dead weight of the concrete structure will be automatically calculated by the program takingcross-sectional area, beam element length, plate element area and thickness as well as specificweight of corresponding material group into account.

The machine masses have been eliminated for this load case.

total weight of concrete: G = 12286 kN


33/120




3.3.2 Load Case 2 Machine Loads

The loads are taken from SIEMENS doc. n 1CSD420784.They are distributed as single loads acting on nodal points in global z-direction :

machine

weight

node Fz

no. kN

C1 1101 -175

C2 1102 -175

C3 1103 -175

C4 1104 -175

C5 1105 -175

C6 1106 -175

C7 1107 -175

C8 1108 -175C9 1109 -175

C10 1110 -175

C11 1111,1112 -313

C12 1113,1114 -313

C13 1115 -63

C14 1116 -63

C15 1117

generator loads

position

machine

weight

node Fz

no. kN

E1 1201 -314.2

E2 1202 -314.2

E3 1203 -85.8

E4 1204 -85.8

E5 1205 -85.8

E6 1206 -85.8

E7 1207 -85.8

E8 1208 -85.8E9 1209 -85.8

E10 1210 -85.8

E11 1211 -85.8

E12 1212 -85.8

E13 1213 -85.8

E14 1214 -85.8

E15 1215

E16 1216

E17 1217

turbine loads

position

load resultant: Fz= -4160 kN

XY

Z 175.175.

175.175.

175.175.175.

175.175.

175.

156.5

156.5

156.5

156.5

63.

63.

314.2

314.2

85.885.885.885.8

85.885.8

85.885.885.885.8

85.885.8

V2

L2

C1

G3


34/120




3.3.3 Load Case 3 Condenser Loads


condenser

forces

node Fz

no. kNm

E1 1201

E2 1202

E3 1203 -47.6

E4 1204 -47.6

E5 1205 -47.6

E6 1206 -47.6

E7 1207 -47.6

E8 1208 -47.6E9 1209 -47.6

E10 1210 -47.6

E11 1211 -47.6

E12 1212 -47.6

E13 1213 -47.6

E14 1214 -47.6

E15 1215

E16 1216

E17 1217

turbine loads

position


XY

Z

47.647.647.647.6

47.647.6

47.647.647.647.647.6

47.6

V2

L3

C1

G3


35/120




3.3.4 Load Case 4 Live Load

A live load of p = 5.0 kN/m is considered acc. to DIN 4024.

The load is applied to all plate elements as an uniformly distributed pressure load in negativez-direction


XY

Z

5.5.5. 5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.5.

5.5.5. 5.

5.5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5. 5.

5.5.5.5.

5.5.5.5.

5.5.5.5.5.

5.5.5.5.

5.5.5.5.

5. 5.5.5.5.

5.5.5.5.

5.

5.5.5. 5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.5.

5.5.5.

5.5.5.5.

5.5.5.5.5.

5.5.5.5.

5.5.5. 5.

5.5.5.5.5.

5.5.5.

5.5.5. 5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.5.

5.5.5. 5.

5.

5.5.5.5.

5.

5.5.5.5.5.

5. 5.5.5.

5.5.5.5.5.5.

5.5.5.5.

5.5.5.5.

5.

5.5.5.5.

5. 5.5.5.5.

5.

5.

5.5.5. 5.

5.5.5.5.

5.5.

5.5.5.5.5.

5.5.5.5.5.

5.

5.5.5.5.5.

5.5.

5.5.5.5.5.

5. 5.5.5.5.

5.5.5. 5.

5.5.5.5.

5.5.

5.5.5.5.5.

5. 5.5.5.5.

5.

5.5.5.5.

5.

5.5.5.5.

5.

5.5.5.

5.

5.5.5. 5.

5.5.5.5.

5.

5.5.5.

5.5.5.

5.5.5.5. 5.

5.5.5.5.

5.

5.5.5. 5.

5.5.5.5.5.

5.5.5. 5.

5.5.5.5.

5.5.5.5.

5.5.5.5.5.

5.

5.5.5.5.

5.5.5.

5.

5.

5.5.5. 5.

5.5.

5.5.5.5.

5.5.5.5.

5.

5.5.5.5.

5.5.5.

5.5.5.5.5.

5.

5.5.5.5.

5.5.5.

5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5.

5. 5.

5.5.5. 5.

5.5.5.

5.5.5.5.

5.5.5.

5.5.5. 5.

5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5.

5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5.

5.5.5.5.

5.5.5.5.

5.5.5.

5.5.5. 5.

5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.

5.5.5. 5.

5.5.5.

5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.5.

5.5.5.5.5.5.5.

5.

5.5.5.5.

5.5.5.

5.5.5. 5.

5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5.

5.5.5.5.5.

5.5.5.5.5.5.

5.5.5.5.

5.5.5.

5.5.5.5.5.

5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.5.

5. 5.5.

5.5.5.

5.5.5.5.

5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.

5.5.5. 5.

5.5.5.

5.5.5.

5.5.5.5.

5.5.5.

5.5.5.5.5.

5.

5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5.

5.5.5.5.5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.

5.5.5.5.5.

5. 5.5.

5.5.5. 5.

5.5.5.5.5.

5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5.

5.5.5.5.5.5.

5.5.5.5.

5.

5.5.5.5.

5.5.

5.5.5.5.

5. 5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5. 5.5.5.

5.5.5.5.

5.5.5.5.

5.

5.5.5.5.

5.5.5.

5.5.5.5.5.

5. 5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5. 5.

5.5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5. 5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5.5.

5.5.5. 5.

5.5.5.5.5.

5.5.5.5.

5.5.5.5.

5. 5.5.5.5.

5.5.5.5.

5.5.5.5.

.

5.5.5.5.

5.5.5.

5.5.5.5.

5.5.5.

5.5.5.5.

5.5.5.5.

V2

L4

C1

G3


36/120




3.3.5 Load Case 5 Power Torque


torque

node Fz

no. kN

C1 1101 27.9

C2 1102 -27.9

C3 1103 27.9

C4 1104 -27.9

C5 1105 27.9

C6 1106 -27.9

C7 1107 27.9

C8 1108 -27.9C9 1109 27.9

C10 1110 -27.9

C11 1111,1112

C12 1113,1114

C13 1115

C14 1116

C15 1117

generator loads

position

torque

node Fz

no. kN

E1 1201 -134.9

E2 1202 134.9

E3 1203 -7.2

E4 1204 7.2

E5 1205 -7.2

E6 1206 7.2

E7 1207 -7.2

E8 1208 7.2E9 1209 -7.2

E10 1210 7.2

E11 1211 -7.2

E12 1212 7.2

E13 1213 -7.2

E14 1214 7.2

E15 1215

E16 1216

E17 1217

turbine loads

position

load resultant: Mx0

XY

Z

27.927.9

27.927.9

27.9

27.927.9

27.927.9

27.9

134.9

134.9

7.27.2

7.27.27.27.2

7.27.27.27.2

7.27.2

V2

L5

C1

G3


37/120




3.3.6 Load Case 6 Thermal Forces X

The loads are taken from SIEMENS doc. n 1CSD420784.

They are distributed as single loads acting on nodal points in global x-direction, taking into accountmoments due to vertical eccentricity:

node Fx My=Fx*ez

no. kN kNm

C1 1101 -112 -157

C2 1102 -112 -157

C3 1103 -112 -157

C4 1104 -112 -157

C5 1105 -112 -157

C6 1106 -112 -157C7 1107 -112 -157

C8 1108 -112 -157

C9 1109 -112 -157

C10 1110 -112 -157

C11 1111,1112 1570 2198

C12 1113,1114 -224 -314

C13 1115 -112 -157

C14 1116 -112 -157

C15 1117

generator loads thermal forces X

position

node Fx My=Fx*ez

no. kN kNm

E1 1201 -21.8 -61

E2 1202 -21.8 -61

E3 1203 -21.5 -30

E4 1204 -21.5 -30

E5 1205 -21.5 -30

E6 1206 -21.5 -30E7 1207 -21.5 -30

E8 1208 -21.5 -30

E9 1209 21.5 30

E10 1210 21.5 30

E11 1211 21.5 30

E12 1212 21.5 30

E13 1213 21.5 30

E14 1214 21.5 30

E15 1215 86.2 121

E16 1216 86.2 121

E17 1217

turbine loads

position

thermal forces X

XY

Z

112.

112.

112.

112.

112.

112.

112.

112.

112.

112.

112.

112.

112.

112.157.

157.

157.

157.

157.

157.

157.

157.

157.

157.

157.

157.

157.

157.

785.

785.

1099.

1099. 21.8

21.8

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

86.2

86.2

61.

61.

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

121.

121.

V2

L6

C1

G6


38/120




3.3.7 Load Case 7 Thermal Forces Y


They are distributed as single loads acting on nodal points in global y-direction, taking into accountmoments due to vertical eccentricity:

node Fy Mx=-Fy*ez

no. kN kNm

C1 1101 112 -157

C2 1102 -112 157

C3 1103 112 -157

C4 1104 -112 157

C5 1105 112 -157

C6 1106 -112 157C7 1107 112 -157

C8 1108 -112 157

C9 1109 112 -157

C10 1110 -112 157

C11 1111,1112 393 -550

C12 1113,1114 224 -314

C13 1115 -112 157

C14 1116 -112 157

C15 1117 -393 550

generator loads thermal forces Y

position

node Fy Mx=-Fy*ez

no. kN kNm

E1 1201

E2 1202

E3 1203 21.5 -30

E4 1204 -21.5 30

E5 1205 21.5 -30

E6 1206 -21.5 30E7 1207 21.5 -30

E8 1208 -21.5 30

E9 1209 21.5 -30

E10 1210 -21.5 30

E11 1211 21.5 -30

E12 1212 -21.5 30

E13 1213 21.5 -30

E14 1214 -21.5 30

E15 1215

E16 1216

E17 1217

turbine loads

position

thermal forces Y

XY

Z

112.112.

112.112.

112.

112.112.

112.112.

112.

112.

112.

196.5196.5

112.

112.

393.

157.157.

157.157.

157.

157.

157.

157.157.

157.157.

157.

157.

157.

275.

275.

550.

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

21.5

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

30.

V2

L7

C1

G6


39/120




3.3.8 Load Case 8 Thermal Forces Z


They are distributed as single loads acting on nodal points in global z-direction, taking into accountmoments due to vertical eccentricity:

node Fz My

no. kN kNm

E1 1201 -49.7

E2 1202 -49.7

E3 1203 6.9

E4 1204 6.9

E5 1205E6 1206

E7 1207

E8 1208

E9 1209

E10 1210

E11 1211

E12 1212

E13 1213 -6.9

E14 1214 -6.9

E15 1215

E16 1216

E17 1217

turbine loads

position

thermal forces Z

XY

Z

6.9

6.9

6.9

6.9

49.7

49.7

V2

L8

C1

G6


40/120




3.3.9 Load case 9 Pipe Forces X


They are distributed as single loads acting on nodal points in global x-direction, taking into accountmoments due to vertical eccentricity.

For determination of design forces the internal forces caused by this load case have to beconsidered with alternating signs.

node Fx My=Fx*ez

no. kN kNm

E1 1201

E2 1202

E3 1203E4 1204

E5 1205

E6 1206

E7 1207

E8 1208

E9 1209

E10 1210

E11 1211

E12 1212

E13 1213

E14 1214

E15 1215 82.5 116

E16 1216 82.5 116

E17 1217

turbine loads

position

pipe forces X

XY

Z

82.5

82.5

116.

116.

V2

L9

C1

G6


41/120




3.3.10 Load case 10 Pipe Forces Y


They are distributed as single loads acting on nodal points in global y-direction, taking into accountmoments due to vertical eccentricity:


node Fy Mx=-Fy*ez

no. kN kNm

E1 1201 31.3 -88

E2 1202 31.3 -88

E3 1203E4 1204

E5 1205

E6 1206

E7 1207

E8 1208

E9 1209

E10 1210

E11 1211

E12 1212

E13 1213

E14 1214

E15 1215

E16 1216

E17 1217 102.5 -103

turbine loads

position

pipe forces Y

XY

Z

31.3

31.3

102.5

88.

88.

103.

V2

L10

C1

G6


42/120




3.3.11 Load case 11 Pipe Forces Z


They are distributed as single loads acting on nodal points in global z-direction.


pipe

forces Z

node Fz

no. kN

E1 1201 98.4

E2 1202 98.4

E3 1203 37.2

E4 1204 37.2E5 1205 11

E6 1206 11

E7 1207 11

E8 1208 11

E9 1209 11

E10 1210 11

E11 1211 11

E12 1212 11

E13 1213 11

E14 1214 11

E15 1215 37.2

E16 1216 37.2

E17 1217

turbine loads

position

XY

Z

98.4

98.4

37.2

37.2

37.2

37.2

11.

11.

11.

11.

11.

11.

11.

11.

11.

11.

V2

L11

C1

G6


43/120




3.3.12 Load case 12 - Erection load

The loads are taken from SIEMENS drawing n 0-13100-B6151. They are distributed as singleloads acting on nodal points in global directions :

node Fx My=Fx*ez Fy Mx=-Fy*ez

no. kN kNm kN kNm

C1 1101 -625 -875 625 -875

C2 1102 -625 -875 -625 875

C9 1109 625 875 625 -875

C10 1110 625 875 -625 875

position

erection loadsgenerator loads

node Fx My=Fx*ez Fy Mx=-Fy*ez

no. kN kNm kN kNm

E3 1203 -257 -360 257 -360

E4 1204 -257 -360 -257 360

E13 1213 257 360 257 -360

E14 1214 257 360 -257 360

turbine loads erection loads

position

XY

Z

625.

625.

625.

625.

257.

257.

257.

257.

875.

875.

875.

875.

360.

360.

360.

360.

625.

625.

625.

625.875.

875.

875.

875.

257.

257.

257.

257.

360.

360.

360.

360.

V2

L18

C1

G6


44/120


45/120




3.3.14 Load case 14 - Loss of blade Y



node Fy Mx=-Fy*ez Fz

no. kN kNm kN

E1 1201 1269.5 -3555 -2724.2

E2 1202 1269.5 -3555 2724.2

E3 1203

E4 1204

E5 1205

E6 1206E7 1207

E8 1208

E9 1209

E10 1210

E11 1211

E12 1212

E13 1213

E14 1214

E15 1215

E16 1216

E17 1217 5903.1 -5903

turbine loads

position

loss of blade Y

XY

Z

1269.5

1269.5

5903.1

2724.2

2724.2

3555.

3555.

5903.

V2

L12

C1

G6


46/120




3.3.15 Load case 15 - Loss of blade Z



loss of

blade Z

node Fz

no. kN

E1 1201 1269.5

E2 1202 1269.5

E3 1203 491.9

E4 1204 491.9

E5 1205 491.9

E6 1206 491.9E7 1207 491.9

E8 1208 491.9

E9 1209 491.9

E10 1210 491.9

E11 1211 491.9

E12 1212 491.9

E13 1213 491.9

E14 1214 491.9

E15 1215

E16 1216

E17 1217

turbine loads

position

XY

Z

1269.5

1269.5

491.9491.9491.9491.9

491.9491.9

491.9491.9491.9491.9

491.9491.9

V2

L13

C1

G6


47/120


48/120




3.3.17 Load case 17 - Seismic load X

Relevant machine loads caused by seismic activities are taken from SIEMENS drawing n1CSD420784. The dead load of foundation is considered by multiplying with the horizontal seismic

acceleration coefficient = 0.200 g as determined in clause [1.9]of the present paper. All loadingsare acting in global x-direction.


node Fx My=Fx*ez

no. kN kNm

C1 1101 17.1 24

C2 1102 17.1 24

C3 1103 17.1 24C4 1104 17.1 24

C5 1105 17.1 24

C6 1106 17.1 24

C7 1107 17.1 24

C8 1108 17.1 24

C9 1109 17.1 24

C10 1110 17.1 24

C11 1111,1112 51.3 72

C12 1113,1114 34.2 48

C13 1115 17.1 24

C14 1116 17.1 24

C15 1117

seismic loads Xgenerator loads

position

node Fx My=Fx*ez

no. kN kNm

E1 1201 123.1 345

E2 1202 123.1 345

E3 1203E4 1204

E5 1205

E6 1206

E7 1207

E8 1208

E9 1209

E10 1210

E11 1211

E12 1212

E13 1213

E14 1214

E15 1215

E16 1216

E17 1217

seismic loads Xturbine loads

position

XY

Z

17.1

17.1

17.1

17.1

17.1

17.1

17.1

17.1

17.1

17.1

25.65

25.65

17.1

17.1

17.1

17.124.

24.

24.

24.

24.

24.

24.

24.

24.

24.

36.

36.

24.

24.

24.

24.

123.1

123.1345.

345.

V2

L15

C1

G6


49/120




3.3.18 Load case 18 - Seismic load Y


acceleration coefficient = 0.200 g as determined in clause [1.9]of the present paper. All loadingsare acting in global y-direction.


node Fy Mx=-Fy*ez

no. kN kNm

C1 1101 16.2 -23

C2 1102 16.2 -23

C3 1103 16.2 -23C4 1104 16.2 -23

C5 1105 16.2 -23

C6 1106 16.2 -23

C7 1107 16.2 -23

C8 1108 16.2 -23

C9 1109 16.2 -23

C10 1110 16.2 -23

C11 1111,1112 48.5 -68

C12 1113,1114 32.3 -45

C13 1115 16.2 -23

C14 1116 16.2 -23

C15 1117 16.2 -23

seismic loads Ygenerator loads

position

node Fy Mx=-Fy*ez

no. kN kNm

E1 1201 36.5 -102

E2 1202 36.5 -102

E3 1203E4 1204

E5 1205

E6 1206

E7 1207

E8 1208

E9 1209

E10 1210

E11 1211

E12 1212

E13 1213

E14 1214

E15 1215

E16 1216

E17 1217 119.7 -120

seismic loads Yturbine loads

position

XY

Z

16.2

16.2

16.2

16.2

16.2

16.2

16.2

16.2

16.2

16.2

24.3

24.3

16.2

16.2

16.2

16.223.

23.

23.

23.

23.

23.

23.

23.

23.

23.

34.5

34.5

23.

23.

23.

23.

36.5

36.5

119.7

102.

102.

120.

16.2

23.

V2

L16

C1

G6


50/120




3.3.19 Load case 19 - Seismic load Z


acceleration coefficient = 0.133 g as determined in clause [1.9]of the present paper. All loadingsare acting in global z-direction.


seismic

loads Z

node Fz

no. kN

C1 1101 16.6

C2 1102 16.6

C3 1103 16.6C4 1104 16.6

C5 1105 16.6

C6 1106 16.6

C7 1107 16.6

C8 1108 16.6

C9 1109 16.6

C10 1110 16.6

C11 1111,1112 33.2

C12 1113,1114 33.2

C13 1115 16.6

C14 1116 16.6

C15 1117

generator loads

position

seismic

loads Z

node Fz

no. kN

E1 1201 78.4

E2 1202 78.4

E3 1203 30.6E4 1204 30.6

E5 1205 2.9

E6 1206 2.9

E7 1207 2.9

E8 1208 2.9

E9 1209 2.9

E10 1210 2.9

E11 1211 2.9

E12 1212 2.9

E13 1213 30.6

E14 1214 30.6

E15 1215

E16 1216

E17 1217

turbine loads

position

XY

Z

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

16.6

78.4

78.4

30.6

30.6

30.6

30.6

2.9

2.9

2.9

2.9

2.9

2.9

2.9

2.9

V2

L17

C1

G6


51/120




3.3.20 Load Case 20 to 31 Seismic Combinations

Seismic forces are combined for 100% acceleration in one direction and 30% in the other twoorthogonal directions. The according superpositions of load case 16 to 18 are stored as load case

numbers 19 to 30.

3.3.21 Load Case 32 to 37 Dynamic Loads at Malfunctional States

The displacements and internal forces and moments which result from the excitation of the naturalmodes of vibration are stored as load case 32 to 37. For the scaling of the mode shapes tomaximum amplitudes refer to clause2.4.


52/120




3.4 Superposition of Load Cases

For the determination of design load cases the single load cases are taken into account acc. to thefollowing superposition schema.

For operational loads a unique safety factor of = 1.50 acc. to IS 456 has been used whichenvelopes the factors defined in DIN 1045-1. For emergency load combinations a reduced factorof = 1.00 can be considered for all related load cases acc. to DIN 1045-1.

operation erection emergency

f f f

1 G 0.90 / 1.50 0.90 / 1.50 1.00

2 G 0.90 / 1.50 0.90 / 1.50 1.00

3 Q 1.50 1.50 1.00

4 Q 1.50 1.50 1.00

5 Q 1.50 - 1.00

6 W 1.50 - 1.007 W 1.50 - 1.00

8 W 1.50 - 1.00

9 W 1.50 - 1.00

10 W 1.50 - 1.00

11 W 1.50 - 1.00

12 M - 1.50 -

13 M - 1.50 -

14 A - - 1.00

15 A - - 1.00

16 A - - 1.00

17 A - - 1.00

18 A - - 1.00

19 A - - 1.00

20 A - - 1.00

21 A - - 1.00

22 A - - 1.00

23 A - - 1.00

24 A - - 1.00

25 A - - 1.00

26 A - - 1.00

27 A - - 1.00

28 A - - 1.00

29 A - - 1.0030 A - - 1.00

31 A - - 1.00

32 dynamic loads mode 12 A - - 1.00




36 A - - 1.00

37 A - - 1.00

load case description

loss of blade (+/-Y)

dead load

machine load

live load 5 kN/m

operational torque

thermal forces X

erection load

type

design combination

seismic X + 0.3 Y + 0.3 Z

seismic X + 0.3 Y - 0.3 Z

seismic X - 0.3 Y + 0.3 Z

seismic X - 0.3 Y - 0.3 Z

seismic Y + 0.3 X + 0.3 Z

horizontal pipe forces (+/-Y)

seismic load +/-Y

seismic load +/-Z

short circuit

loss of blade (+/-Z)

erection load

seismic load +/-X

seismic Z + 0.3 X + 0.3 Y



seismic Z + 0.3 X - 0.3 Yseismic Z - 0.3 X + 0.3 Y

seismic Z - 0.3 X - 0.3 Y

horizontal pipe forces (+/-X)

condenser load

thermal forces Y

thermal forces Z

vertical pipe forces (+/-Z)

seismic Y + 0.3 X - 0.3 Z

seismic Y - 0.3 X + 0.3 Z

seismic Y - 0.3 X - 0.3 Z

load case types: G permanent loadQ non-permanent load

W non-permanent load with alternating signs ()A alternative load with alternating signs ()M erection load, alternative to all other non-permanent loads


53/120




This procedure leads to the following 48 design load cases:

LC X01: max nxx LC X09: min nxxLC X02: max nyy LC X10: min nyyLC X03: max n

xy LC X11: min n

xy

LC X04: max qxz LC X12: min qxzLC X05: max mxx LC X13: min mxxLC X06: max myy LC X14: min myyLC X07: max mxy LC X15: min mxyLC X08: max qyz LC X16: min qyz

where: X=1 for operation combinationX=2 for erection combinationsX=3 for emergency combinations


54/120




3.5 Design Forces and Moments

The reinforcement design is performed within the local coordinate system of the plate

elements.

The local coordinate systems corresponds to the global coordinates, i. e. the local z-axis isdirected upwardly.

The maximum required reinforcement for the load cases mentioned in clause (3.4)will bedetermined.

The sign convention of the internal forces for plate elements is shown below (acc. to DIN1080).

Sign convention of internal plate forces & moments:

The distributions of the calculated maximum und minimum plate moments mxxand myyare shownexemplarily on the following pages.


55/120




3.5.1 Design Moments due to Operational Combinations

plate moments mxx

X

Y

Z

2098.

1913.

1727.

1542.

1357.

1172.

987.

801.9

616.8

431.7

246.6

61.51

-123.6

-308.7

-493.8

-678.9

-864.

V5

C1

G3

Output Set: MAX Mxx

Contour: Plate X Moment

X

Y

Z

618.1378.

138.

-102.1

-342.2

-582.2

-822.3

-1062.

-1302.

-1542.

-1783.

-2023.

-2263.

-2503.

-2743.

-2983.

-3223.

V5

C1G3

Output Set: MIN Mxx



56/120




plate moments myy

X

Y

Z

329.8

194.5

59.12

-76.24

-211.6

-347.

-482.3

-617.7

-753.

-888.4

-1024.

-1159.

-1294.

-1430.

-1565.

-1701.

-1836.

V5

C1

G3

Output Set: MAX Myy

Contour: Plate Y Moment

X

Y

Z

105.

-202.1

-509.2

-816.3

-1123.

-1430.

-1738.

-2045.

-2352.

-2659.

-2966.

-3273.

-3580.

-3887.

-4194.

-4501.

-4809.

V5

C1

G3

Output Set: MIN Myy



57/120




3.5.2 Design Moments due to Erection Combinations

plate moments mxx

X

Y

Z

2911.

2662.

2413.

2164.

1915.

1667.

1418.

1169.

919.9

670.9

422.

173.1

-75.78

-324.7

-573.6

-822.5

-1071.

V5

C1

G3

Output Set: MAX Mxx


X

Y

Z

810.4379.9

-50.59

-481.1

-911.6

-1342.

-1773.

-2203.

-2634.

-3064.

-3495.

-3925.

-4356.

-4786.

-5217.

-5647.

-6078.

V5

C1G3

Output Set: MIN Mxx



58/120




plate moments myy

X

Y

Z

600.3

438.

275.6

113.3

-49.01

-211.3

-373.7

-536.

-698.3

-860.6

-1023.

-1185.

-1348.

-1510.

-1672.

-1835.

-1997.

V5

C1

G3

Output Set: MAX Myy


X

Y

Z

154.5

-139.7

-433.9

-728.2

-1022.

-1317.

-1611.

-1905.

-2199.

-2494.

-2788.

-3082.

-3376.

-3671.

-3965.

-4259.

-4553.

V5

C1

G3

Output Set: MIN Myy



59/120




3.5.3 Design Moments due to Emergency Combinations

plate moments mxx

X

Y

Z

3820.

3562.

3305.

3048.

2791.

2534.

2277.

2020.

1763.

1505.

1248.

991.1

734.

476.9

219.7

-37.41

-294.5

V5

C1

G3

Output Set: MAX Mxx


X

Y

Z

400.9-17.15

-435.2

-853.3

-1271.

-1689.

-2107.

-2526.

-2944.

-3362.

-3780.

-4198.

-4616.

-5034.

-5452.

-5870.

-6288.

V5

C1G3

Output Set: MIN Mxx



60/120




plate moments myy

X

Y

Z

2117.

1906.

1695.

1484.

1272.

1061.

849.6

638.3

426.9

215.6

4.326

-207.

-418.3

-629.6

-840.9

-1052.

-1264.

V5

C1

G3

Output Set: MAX Myy


X

Y

Z

18.18

-340.7

-699.6

-1058.

-1417.

-1776.

-2135.

-2494.

-2853.

-3212.

-3571.

-3929.

-4288.

-4647.

-5006.

-5365.

-5724.

V5

C1

G3

Output Set: MIN Myy



61/120




3.6 Design of Reinforcement

The foundation plate is designed for the maximum values of internal forces, which are determined

as described in clause (3.4).

3.6.1 Building materials

Concrete: Grade (IS 456 - 2000) M 35Compressive strength fck= 35 N/mmDesign strength fcd= 23.45/ 1.5 = 15.6 N/mmStatic modulus of elasticity Ec= 29580 MN/m

Density of reinforced concrete = 25 kN/mPoissons ratio = 0.20

Reinforcing Steel: Grade (IS 1786 - 1985) Fe 415Yield strength fyk= 415 MN/mDesign strength fyd= 415 MN/m / 1.15 = 360 N/mmModulus of elasticity 210000 MN/m

3.6.2 Calculation method

The reinforcement design is performed according to the German standard DIN 1045-1.The design forces of the different reinforcement layers are calculated acc. to the method of

Baumann(3).

First the internal forces and moments are converted to normal forces in both outer layers (+z/-z) of

the plate. The stati