Damage evolution in EB-PVD thermal barrier coatings for turbine blades in aircraft engines under close to reality testing conditions

被引：1

作者：

Bartsch, M ^{[1
]}

Marci, G ^{[1
]}

Mull, K ^{[1
]}

Sick, C ^{[1
]}

机构：

[1] German Aerosp Ctr, DLR, Inst Mat Res, D-51147 Cologne, Germany

来源：

INTERNATIONAL JOURNAL OF MATERIALS & PRODUCT TECHNOLOGY | 2001年 / 16卷 / 1-3期

关键词：

thermal barrier coating; zirconia; turbine blade; damage mechanism; lifetime prediction; thermal gradient;

D O I：

10.1504/IJMPT.2001.005437

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

In advanced gas turbines for aircraft engines, internally cooled turbine blades have a ceramic thermal barrier coating (TBC) to reduce the thermal load of the metallic substrate. Exhausting the full potential of the TBC to increase the turbine inlet temperature requires reliable lifetime prediction methods, since failure of the TBC will entail the immediate failure of the blade. A lifetime prediction concept for TBC's based on lifetime analyses of close to reality tests is given. Basic idea is to ensure that failure mechanisms during testing are the same as in an turbine engine. Specimens with an electron beam physical vapour deposited (EB-PVD) TBC were tested under realistic fatigue road but drastically reduced holding times. The results exhibited that the as-coated properties of the ceramic coating are sufficient to survive the required load alternations in service. The influence of kinetic damage mechanisms on the TBC-lifetime will be determined in tests with pre-aged specimens.

引用

页码：248 / 257

页数：10

共 15 条

[1] ARANA M, 1999, P TBC WINT WORKSH JA
[2] Bartsch M, 1999, ADV ENG MATER, V1, P127, DOI 10.1002/(SICI)1527-2648(199910)1:2<127::AID-ADEM127>3.0.CO
[3] 2-6
[4] FRITSCHER K, 1999, DLR I MAT RES
[5] GOWARD GW, 1998, PROGR, V108, P73
[6] Effects of morphology on the decohesion of compressed thin films
He, MY
Evans, AG
Hutchinson, JW
[J]. MATERIALS SCIENCE AND ENGINEERING A-STRUCTURAL MATERIALS PROPERTIES MICROSTRUCTURE AND PROCESSING, 1998, 245 (02): : 168 - 181
[7] Kaden U, 1999, ELEVATED TEMPERATURE COATINGS: SCIENCE AND TECHNOLOGY III, P27
[8] KAYASSER WA, 1999, P 7 INT C FAT 99 P R, V3, P1897
[9] New testing facility and concept for life prediction of TBC turbine engine components
Marci, G
Mull, KM
Sick, C
Bartsch, M
[J]. THERMO-MECHANICAL FATIGUE BEHAVIOR OF MATERIALS, 3RD VOL, 2000, 1371 : 296 - 303
[10] MARICOCCHI A, 1995, NASA C PUBLICATION, V3312, P79

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