Creep-Fatigue Life Evaluation Method for Perforated Plates at Elevated Temperature

[+] Author and Article Information
Osamu Watanabe1

Department of Engineering Mechanics and Energy, Graduate School of Systems and Information Engineering, University of Tsukuba, Tsukuba, Ibaraki 305-8573, Japanwatanabe@kz.tsukuba.ac.jp

Takuya Koike

 Nuclear Safety Regulatory Standards Division, Nuclear and Industrial Safety Agency, Ministry of Economy, Trade and Industry, Kasumigaseki, Tokyo 100-8986, Japan


Corresponding author.

J. Pressure Vessel Technol 128(1), 17-24 (Oct 15, 2005) (8 pages) doi:10.1115/1.2137766 History: Received September 30, 2005; Revised October 15, 2005

The accurate evaluation scheme for creep-fatigue strength is one of the continuing main issues for elevated temperature design; particularly, the three-dimensional structure having stress concentration is becoming more important. The present paper investigates fatigue strength and creep-fatigue strength of perforated plate having stress concentration as an example. The specimens are made of type 304 SUS stainless steel, and the temperature is kept to 550°C. The whole cycles of the experiment record are analyzed, and the characteristics of the structure having stress concentration are discussed. The present paper employs stress redistribution locus (abbreviated as SRL) in evaluation plastic behavior in cyclic fatigue process as well as stress relaxation in creep process, and the feasibility is discussed in conjunction with the comparison to experimental results.

Copyright © 2006 by American Society of Mechanical Engineers
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Figure 1

Geometry and dimensions of test specimens

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Figure 2

Experimental setup

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Figure 3

Assumed load wave in the trapezoidal shape

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Figure 4

Experimental result for fatigue test at 550°C

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Figure 5

Strain estimated by Neuber’s law and SRL method

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Figure 6

Fatigue test of strain and failure cycle relation by SRL method

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Figure 7

History of tensile load of perforated plates C1

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Figure 8

History of tensile load of smoothed plates C0

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Figure 9

Load decrease and stress-strain loop at 1000th and 2000thcycle of C1 model

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Figure 10

Crack tip at the hole side of C1 specimen(Load (Lpeak∕Lmax) and magnification are (a) 94%, 50; (b) 98%, 500; and (c) 99%, 500)

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Figure 11

History of tensile load in multispecimen method of C1 model for 1.0% straining

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Figure 12

Derivation of crack initiation cycle Nc from the experimental result

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Figure 13

Strain amplitude versus cycle relation by use of SRL method

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Figure 14

Load history in the trapezoidal shape with tensile holding

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Figure 15

Creep-fatigue test result in nominal strain versus failure cycle number

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Figure 16

Crack initiation near hole side in creep-fatigue test of C1 with 1.0% nominal strain amplitude and 0.1h holding at 97% load reduction. (a) magnification 500; (b) 200.

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Figure 17

Creep-fatigue test result

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Figure 18

Relaxation locus in SRL method

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Figure 19

Relaxation locus of smoothed plate during 1h under nominal strain amplitude of 1.0%.

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Figure 20

Comparison of creep-fatigue damage by SRL method in creep behavior

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Figure 21

Prediction of crack initiation life by SRL method

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Figure 22

Ratio of creep-fatigue life by elastic follow-up method and SRL method

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Figure 23

Ratio of life by the previous method and the proposed method



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