Failure of gas turbine blades

被引：50

作者：

Gallardo, JM ^{[1
]}

Rodríguez, JA ^{[1
]}

Herrera, EJ ^{[1
]}

机构：

[1] Univ Sevilla, Grp Met & Ingn Mat, ES Ingn, Seville 41092, Spain

来源：

WEAR | 2002年 / 252卷 / 3-4期

关键词：

gas-turbine failure; wear; thermal expansion; coating failure;

D O I：

10.1016/S0043-1648(01)00885-7

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

The first-stage blades of a gas turbine had suffered a severe deterioration after around 10 500 h service. The expected service life was 40 000 h. Failure analysis (visual observations, studies by optical microscopy, scanning electron microscopy (SEM), SEM back-scattered electron (SEM-BSE), EDX, X-ray diffraction (XRD) and dimensional metrology) has been carried out. Blades, manufactured in the nickel superalloy CMSX-4, lost the protective coatings from their tips due to wear. Unprotected surfaces suffered high-temperature hot corrosion (Type-I corrosion). It is concluded that failure was mainly caused by an uneven clearance (out-of-line) between rotor and lining. (C) 2002 Elsevier Science B.V. All rights reserved.

引用

页码：264 / 268

页数：5

共 13 条

[1]

*ALL, 1987, ALL HDB LOSS PREV, P385

[2]

*ASM, 1987, ASM MET HDB, V13, P1000

[3]

*ASM INT, 1990, ASM MET HDB, V1, P995

[4]

ELSNER W, 1998, ALLIANZ REP, V2, P97

[5]

ERICKSON GL, 1997, ADV MATER PROCESS, V3, P27

[6] Progress in coatings for gas turbine airfoils [J].

Goward, GW .

SURFACE & COATINGS TECHNOLOGY, 1998, 108 (1-3) :73-79

[7]

GOWARD GW, 1988, T ASME, V110, P150

[8]

LEHNERT G, 1972, ELECTRODEPOSITION SU, V1, P189

[9]

RESTALL JE, 1986, MAT SCI TECHNOL, V12, P2625

[10]

SMITH WF, 1981, STRUCTURE PROPERTIES, P485

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