fsefea.comfsefea.com/wp-content/uploads/2017/11/Example1_report.docx · Web viewDescription. Parameter. Value for Expansion Joint. Value for Shell. Material. Mat. SA 240 304L . SA

Program : FSE 1.0

Analysis Time Stamp : Mon Nov 20 15:20:11 2017

Working Directory : C:/FSE_JOBS/Examples

Job Name : Example1

Design Code : ASME Sec VIII Div I - 2017 Ed.

Inputs :

Geometry ParametersDescription Parameter ValueExchanger Shell ID G 1330 mmExchanger Shell Thk Ts 13 mmExpansion Joint ID ID 1600 mmExpansion Joint Thk Te 16 mmInner Torus Radius Ra 48 mmOuter Torus Radius Rb 48 mmNumber of Convolutions Nfse 3Exchanger Shell Length Li 500 mmTransition Piece Length Lt 50 mmInside Straight Flange Length Fa 25 mmOutside Straight Flange Length Fb 36 mmAnnular Plate Straight Length La 20 mm

Material PropertiesDescription Parameter Value for

Expansion Joint

Value for Shell

Material Mat SA 240 304L SA 516 Gr 70Young's Modulus at Room Temperature E 195000 MPa 202000 MPaPoisson's Ratio v 0.31 0.3Min Yield Stress at Ambient Syamb 170 MPa 260 MPaMin Tensile Stress at Ambient Stamb 485 MPa 485 MPaDesign Temperature Temp 200 deg C 200 deg CAllowable Stress at Design Temperature S 110 MPa 138 MPaYield Stress at Design Temperature Sy 121 MPa 225 MPaIs Design Temperature in Creep Range creep No No

Fatigue DataDescription Parameter Value for

Expansion Joint

Value for Shell

Desired Cycle Life N 1500 1500S-N Curve Data N1 1000 1000S-N Curve Data S1 744.6 MPa 572.3 MPaS-N Curve Data N2 2000 2000S-N Curve Data S2 590.2 MPa 441.3 MPaYoung's Modulus of design fatigue curve Efc 195000 MPa 195000 MPaYoung's Modulus at average temperature of cycle

Et 183000 MPa 192000 MPa

LoadsLoad Case Thermal Loads Internal Pressure

(MPa)Shell Axial Stress

(MPa)1 No -0.1 122 No 1.3 -403 No 1.3 -14 No -0.1 55 Yes 0 1306 Yes 1.3 157 Yes 1.3 108 Yes 0 12

Analysis OptionsDescription Parameter ValueNumber of elements across thickness enum 6FSRF for weld toes FSRF_weld 1.8FSRF for unwelded region FSRF_noweld 1.0Include weld at middle symmetric plane mid_plane_weld Yes

Output Summary :

Spring Rate Determination : Expansion Joint Elastic Axial Stiffness (from FEA) Ke = 150965 N/mm

Stress Ratio Summary TableLoad Case Linearized Von-

Mises Stress RatioLinearized Triaxial

Stress RatioAlternating Stress

Ratio1 0.774 0.511 0.1682 2.567 1.356 0.5763 0.369 0.159 0.1144 0.322 0.209 0.0715 4.206 NA 1.8086 0.536 NA 0.1957 0.391 NA 0.1638 0.388 NA 0.167

Max Stress Ratios 4.206 1.356 1.808NOTES:

Analysis has been carried out for the uncorroded case. Stress Ratios < 1 passes the allowable limits. Triaxial stress limits are checked only for the non-thermal cases as per sec 5.3.2 ASME

Sec VIII Div 2. Stress Linearization procedure is adopted from sec 5-A.4.1 of ASME Sec VIII Div 2. Allowable linearized Von-Mises Stress is taken as 1.5S for mechanical (non-thermal)

load cases as per para 4.20.5 of ASME Sec VIII Div 2 Allowable linearized Von-Mises Stress is taken as SPS for thermal or mechanical +

thermal load cases as per para 4.20.5 of ASME Sec VIII Div 2 Allowable linearized Triaxial Stress is limited to 4S as per para 5.3.2 of ASME Sec VIII

Div 2 Alternating Von-Mises Stress is calculated as Salt = FSRF*(Total Von-Mises Stress/2) Allowable Alternating Von-Mises Stress is obtained by log interpolation of the user

input S-N curve values

Outputs Detailed :

Boundary Condition and Loads for spring rate determination Axial displacement at the left end (mid symmetry plane) is fixed. Axial force corresponding to 100 psi internal pressure is applied at the right shell end

as, Faxial = (100 psi)*(pi/4*G^2) = 957882 N.

Spring Rate Determination Axial displacement of right shell end computed by FEA, delta_axial = 1.0575 mm. Spring rate of axisymmetric model, Kas = Faxial/delta_axial = 905790 N/mm. Equivalent Spring rate for the full model, Ke = Kas/(2*Nfse) = 150965 N/mm.

Boundary Condition and Loads for user defined load cases Axial displacement at the left end (mid symmetry plane) is fixed. "delta_applied" as per below table is applied at the right end of the shell for different

load cases.

Load Case Shell Axial Stress Sax (MPa)

delta = Sax*As/Ke (mm)

delta_applied = delta/(2*Nfse)

(mm)1 12.0 4.3599 0.72662 -40.0 -14.5329 -2.42223 -1.0 -0.3633 -0.06064 5.0 1.8166 0.30285 130.0 47.232 7.8726 15.0 5.4498 0.90837 10.0 3.6332 0.60558 12.0 4.3599 0.7266

NOTE: As = pi*(G+Ts)*Ts is the shell annular area.

Stress Classification Lines (SCLs)SCL Num SCL Location Orientation

(deg)FSRF

1 Left End - Outer Straight Flange 0 1.82 Outer Torus 0 1.03 Outer Torus 22.5 1.04 Outer Torus 45 1.05 Outer Torus 67.5 1.06 Outer Torus 90 1.07 Center of Annular Plate 90 1.08 Inner Torus 90 1.09 Inner Torus 67.5 1.0

10 Inner Torus 45 1.011 Inner Torus 22.5 1.012 Inner Torus 0 1.013 Right End - Inner Straight Flange 0 1.814 Right End - Transition Piece 0 1.8

NOTES :

SCL numbers progressively increase as we move from left (Middle Symmetry Plane) to right (Shell).

SCL orientation is with respect to radial direction. FSRF is Fatigue Strength Reduction Factor.

Stress Analysis Results

Load Case : 1Check for protection against plastic collapse and local failure.

SCL Number

Linearized Von-Mises Stress (MPa)

Allowable Stress (MPa)

Stress Ratio

Linearized Triaxial

Stress (MPa)


Stress Ratio

1 115.0 165.0 0.697 41.9 440.0 0.0952 122.5 165.0 0.742 77.5 440.0 0.1763 127.8 165.0 0.774 113.4 440.0 0.2584 118.9 165.0 0.720 122.0 440.0 0.2775 90.2 165.0 0.547 91.9 440.0 0.2096 45.4 165.0 0.275 13.6 440.0 0.0317 32.7 165.0 0.198 18.6 440.0 0.0428 45.3 165.0 0.275 65.1 440.0 0.1489 99.1 165.0 0.601 161.4 440.0 0.367

10 125.7 165.0 0.762 219.2 440.0 0.49811 121.2 165.0 0.735 225.1 440.0 0.51112 93.7 165.0 0.568 177.4 440.0 0.40313 57.3 165.0 0.347 109.6 440.0 0.24914 29.8 165.0 0.181 60.7 440.0 0.138

Check for protection against failure from cyclic loads.

SCL Number Alternating Von-Mises Stress (MPa)


Stress Ratio

1 102.6 610.0 0.1682 63.3 610.0 0.1043 69.5 610.0 0.1144 65.2 610.0 0.1075 49.2 610.0 0.0816 22.1 610.0 0.0367 14.7 610.0 0.0248 22.9 610.0 0.0389 55.5 610.0 0.091

10 70.9 610.0 0.11611 68.3 610.0 0.11212 48.6 610.0 0.08013 51.0 610.0 0.08414 28.7 484.0 0.059


SCL Number



Stress Ratio

Linearized Triaxial

Stress (MPa)


Stress Ratio

1 393.3 165.0 2.383 556.2 440.0 1.2642 411.1 165.0 2.491 594.6 440.0 1.3513 423.5 165.0 2.567 596.8 440.0 1.3564 397.2 165.0 2.407 526.2 440.0 1.1965 312.8 165.0 1.896 364.7 440.0 0.8296 180.2 165.0 1.092 124.4 440.0 0.2837 139.0 165.0 0.843 115.0 440.0 0.2618 153.8 165.0 0.932 252.6 440.0 0.5749 328.3 165.0 1.990 478.3 440.0 1.087

10 423.3 165.0 2.566 549.7 440.0 1.24911 412.8 165.0 2.502 475.8 440.0 1.08112 312.4 165.0 1.894 303.7 440.0 0.69013 182.3 165.0 1.105 97.0 440.0 0.22014 84.0 165.0 0.509 -32.4 440.0 -0.074




Stress Ratio

1 351.2 610.0 0.5762 211.5 610.0 0.3473 228.8 610.0 0.3754 216.2 610.0 0.3555 169.3 610.0 0.2786 89.2 610.0 0.1467 64.8 610.0 0.1068 74.4 610.0 0.1229 183.0 610.0 0.300

10 238.2 610.0 0.39111 232.6 610.0 0.38112 164.7 610.0 0.27013 141.7 610.0 0.23214 85.2 484.0 0.176


SCL Number



Stress Ratio

Linearized Triaxial

Stress (MPa)


Stress Ratio

1 34.9 165.0 0.211 43.1 440.0 0.0982 36.5 165.0 0.221 55.3 440.0 0.1263 39.3 165.0 0.238 63.2 440.0 0.1444 40.3 165.0 0.245 55.6 440.0 0.1265 41.6 165.0 0.252 49.4 440.0 0.1126 47.4 165.0 0.287 65.9 440.0 0.1507 49.8 165.0 0.302 70.0 440.0 0.1598 51.1 165.0 0.310 70.2 440.0 0.1599 50.2 165.0 0.304 56.0 440.0 0.127

10 49.8 165.0 0.302 48.9 440.0 0.11111 55.2 165.0 0.335 61.2 440.0 0.13912 55.5 165.0 0.336 59.8 440.0 0.13613 53.8 165.0 0.326 49.6 440.0 0.11314 60.9 165.0 0.369 49.6 440.0 0.113




Stress Ratio

1 31.8 610.0 0.0522 18.1 610.0 0.0303 19.3 610.0 0.0324 19.9 610.0 0.0335 20.6 610.0 0.0346 23.9 610.0 0.0397 25.0 610.0 0.0418 25.4 610.0 0.0429 25.1 610.0 0.041

10 24.9 610.0 0.04111 28.1 610.0 0.04612 27.9 610.0 0.04613 48.0 610.0 0.07914 55.0 484.0 0.114


SCL Number



Stress Ratio

Linearized Triaxial

Stress (MPa)


Stress Ratio

1 48.5 165.0 0.294 15.4 440.0 0.0352 51.2 165.0 0.310 29.5 440.0 0.0673 53.1 165.0 0.322 44.0 440.0 0.1004 49.6 165.0 0.300 47.8 440.0 0.1095 38.3 165.0 0.232 36.2 440.0 0.0826 20.6 165.0 0.125 4.7 440.0 0.0117 15.4 165.0 0.093 4.5 440.0 0.0108 18.6 165.0 0.113 23.7 440.0 0.0549 41.1 165.0 0.249 64.1 440.0 0.146

10 52.6 165.0 0.319 89.0 440.0 0.20211 51.0 165.0 0.309 92.2 440.0 0.20912 38.7 165.0 0.234 72.3 440.0 0.16413 23.2 165.0 0.141 43.6 440.0 0.09914 11.2 165.0 0.068 23.0 440.0 0.052




Stress Ratio

1 43.3 610.0 0.0712 26.4 610.0 0.0433 28.8 610.0 0.0474 27.1 610.0 0.0445 20.8 610.0 0.0346 10.1 610.0 0.0177 7.0 610.0 0.0118 9.4 610.0 0.0159 23.0 610.0 0.038

10 29.6 610.0 0.04911 28.7 610.0 0.04712 20.4 610.0 0.03313 19.5 610.0 0.03214 11.0 484.0 0.023


SCL Number Linearized Von-Mises Stress (MPa)


Stress Ratio

1 1235.5 330.0 3.7442 1325.3 330.0 4.0163 1388.1 330.0 4.2064 1288.0 330.0 3.9035 964.8 330.0 2.9246 460.8 330.0 1.3967 323.6 330.0 0.9818 499.2 330.0 1.5139 1079.1 330.0 3.270

10 1359.5 330.0 4.12011 1314.4 330.0 3.98312 1038.2 330.0 3.14613 637.3 330.0 1.93114 353.5 330.0 1.071




Stress Ratio

1 1102.5 610.0 1.8082 685.1 610.0 1.1233 757.3 610.0 1.2424 707.9 610.0 1.1605 527.3 610.0 0.8656 223.0 610.0 0.3667 149.5 610.0 0.2458 253.2 610.0 0.4159 604.9 610.0 0.992

10 766.6 610.0 1.25711 735.3 610.0 1.20612 525.1 610.0 0.86113 586.3 610.0 0.96114 334.6 484.0 0.691




Stress Ratio

1 133.2 330.0 0.4042 154.7 330.0 0.4693 169.4 330.0 0.5134 153.8 330.0 0.4665 103.4 330.0 0.3136 52.5 330.0 0.1597 58.2 330.0 0.1768 82.3 330.0 0.2499 139.1 330.0 0.421

10 173.2 330.0 0.52511 176.9 330.0 0.53612 154.5 330.0 0.46813 124.2 330.0 0.37614 100.2 330.0 0.304




Stress Ratio

1 118.8 610.0 0.1952 81.0 610.0 0.1333 94.4 610.0 0.1554 86.2 610.0 0.1415 57.6 610.0 0.0946 23.6 610.0 0.0397 26.6 610.0 0.0448 42.1 610.0 0.0699 77.6 610.0 0.127

10 90.5 610.0 0.14811 84.1 610.0 0.13812 74.2 610.0 0.12213 113.4 610.0 0.18614 90.1 484.0 0.186




Stress Ratio

1 87.3 330.0 0.2642 105.5 330.0 0.3203 117.8 330.0 0.3574 106.4 330.0 0.3225 72.5 330.0 0.2206 48.1 330.0 0.1467 52.7 330.0 0.1608 66.9 330.0 0.2039 103.5 330.0 0.314

10 126.4 330.0 0.38311 128.9 330.0 0.39112 116.9 330.0 0.35413 100.8 330.0 0.30514 87.9 330.0 0.266




Stress Ratio

1 77.9 610.0 0.1282 55.5 610.0 0.0913 66.1 610.0 0.1084 59.9 610.0 0.0985 38.8 610.0 0.0646 22.6 610.0 0.0377 24.9 610.0 0.0418 34.1 610.0 0.0569 55.8 610.0 0.091

10 62.5 610.0 0.10311 59.6 610.0 0.09812 56.7 610.0 0.09313 91.8 610.0 0.15014 79.1 484.0 0.163




Stress Ratio

1 114.0 330.0 0.3462 122.3 330.0 0.3713 128.1 330.0 0.3884 118.9 330.0 0.3605 89.1 330.0 0.2706 42.5 330.0 0.1297 29.9 330.0 0.0918 46.1 330.0 0.1409 99.6 330.0 0.302

10 125.5 330.0 0.38011 121.3 330.0 0.36812 95.8 330.0 0.29013 58.8 330.0 0.17814 32.6 330.0 0.099




Stress Ratio

1 101.8 610.0 0.1672 63.2 610.0 0.1043 69.9 610.0 0.1154 65.3 610.0 0.1075 48.7 610.0 0.0806 20.6 610.0 0.0347 13.8 610.0 0.0238 23.4 610.0 0.0389 55.8 610.0 0.092

10 70.8 610.0 0.11611 67.9 610.0 0.11112 48.5 610.0 0.07913 54.1 610.0 0.08914 30.9 484.0 0.064

Plots

Axial Displacement for Springrate Determination

Stress Classification Line (SCL) Locations across the thickness

Load Case 1: Axial Displacement Plot

Load Case 1: Von-Mises Stress Plot















Load Case 1: Linearized Stress Plots








Documents

fsefea.comfsefea.com/wp-content/uploads/2017/11/Example1_report.docx · Web viewDescription. Parameter. Value for Expansion Joint. Value for Shell. Material. Mat. SA 240 304L . SA