Research Papers: Gas Turbines: Manufacturing, Materials, and Metallurgy

Thermomechanical Fatigue Behavior of Bare and Coated CMSX-4

[+] Author and Article Information
T. Coppola, S. Riscifuli, O. Tassa

 Centro Sviluppo Materiali S.p.A., Via di Castel Romano 100, Roma 00128, Italy

G. Pasquero

R&D, Avio S.p.A., Via 1 Maggio 56, Rivalta di Torino 10040, Italy

J. Eng. Gas Turbines Power 132(1), 012101 (Sep 29, 2009) (5 pages) doi:10.1115/1.3124666 History: Received April 01, 2008; Revised May 19, 2008; Published September 29, 2009

Highly cooled turbine blades undergo very high thermal gradients during rapid engine idle-max-idle cycling. Traditional isothermal fatigue data are often insufficient for predicting service lives. A complete set of high temperature tests, in the range of 7501050°C, was performed on single crystal alloy CMSX-4. The test program comprised tensile, creep, low cycle fatigue, and thermomechanical fatigue (TMF) tests. In particular the cycle time for TMF was 3 min, aiming to simulate the real high-power transient conditions in aircraft engines. Clockwise and counterclockwise diamond cycle types were applied on bare and coated specimens to investigate their influence on the fatigue limit. The comparison of the results obtained with the available ones from open literature is discussed.

Copyright © 2010 by American Society of Mechanical Engineers
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Figure 3

Tensile test results

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Figure 4

Creep test results

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Figure 1

Temperature versus time cycle for TMF testing

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Figure 7

SEM micrographs of fully heated treated material

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Figure 8

SEM micrograph showing γ′ morphology after creep tests at 1050°C

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Figure 9

SEM micrographs of LCF fracture starting by (a) pore and (b) by surface

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Figure 10

SEM micrographs showing oxide hillocks on the surface of the uncoated TMF specimen

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Figure 11

SEM micrographs showing the TMF fracture of the coated specimen

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Figure 12

Creep test results compared with literature data

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LCF results at R=−1 compared with literature data

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LCF results at R=0 compared with literature data

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Hysteresis loop at the maximum strain

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Area loop at maximum strain versus TMF life

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Figure 17

TMF results compared with literature data

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Figure 18

Cracks in the coating (block D specimen)



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