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TECHNICAL PAPERS: Gas Turbines: Controls, Diagnostics & Instrumentation

Validation of CESI Blade Life Management System by Case Histories and in situ NDT

[+] Author and Article Information
Claudia Rinaldi, Valerio Bicego, Pier Paolo Colombo

 CESI, Via Rubattino 54, 20134 Milano, Italy

J. Eng. Gas Turbines Power 128(1), 73-80 (Mar 01, 2004) (8 pages) doi:10.1115/1.2056534 History: Received October 01, 2003; Revised March 01, 2004

A life management system was developed for hot components of large industrial gas turbines, in the form of a software tool for predicting component lives under typical operational transients (normal and also abnormal) and steady-state periods. The method utilizes results of previous thermo-mechanical finite element and finite volume fluid mechanics analyses. The basic idea of this method is using data from structural and aero-thermal analyses (pressures and temperatures), blade life theory, and material properties as an input to algorithms, and using operational and historical data to validate the predicted damage amounts. The software developed in this project, of general applicability to all GT models, has been implemented with reference to the geometries, materials, and service conditions of a Fiat-Westinghouse model.

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Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Case history 1: distribution of cyclic oxidation damage

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Figure 2

Case history 1: distribution of steady-state temperature

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Figure 3

Case history 1: distribution of thermo-mechanical fatigue damage

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Figure 4

Case history 2: distribution of cyclic oxidation damage

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Figure 5

Case history 2: distribution of thermomechanical fatigue damage

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Figure 6

F-SECT results for blade of case history 2A in Table 1

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Figure 7

Long intergranular stress corrosion cracks at platform edge of blade of case history 2B in Table 1 (see Fig. 8)

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Figure 8

Position of platform crack shown in Fig. 7

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Figure 9

Transgranular cracks at platform edge on blade of case history 2B in Table 1

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Figure 10

Case history 3: cyclic oxidation damage on mounted first stage blades, leading edge side

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Figure 11

Case history 3: damage on first stage blades

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Figure 12

Case history 3: distribution of cyclic oxidation damage

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Figure 13

Case history 3: distribution of thermo-mechanical fatigue damage

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Figure 14

Case history 3: platform TMF cracks at the same location where maximum fatigue damage is shown in Fig. 1

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