Failure investigation of blade and disk in first stage compressor

Engineering Failure Analysis

Volumn 7, Issue 6, 2000, Pages 385-392

  Xi, N S ^a   Zhong, P D ^a   Huang, H Q ^b   Yan, H ^a   Tao, C H ^a  

^a BEIJING INSTITUTE OF AERONAUTICAL MATERIALS   (China)

^b Guizhou Aeroengine Institute   (China)

Author keywords

Engine failures; Fatigue; Gas turbine failures; Turbine blade failures; Turbine disk failures

Indexed keywords

AIRCRAFT ENGINES; COMPRESSORS; COMPUTATIONAL METHODS; CRACKS; DISKS (MACHINE COMPONENTS); FAILURE ANALYSIS; FATIGUE TESTING; FRACTURE TESTING; NONDESTRUCTIVE EXAMINATION; STRESS ANALYSIS; TURBOMACHINE BLADES;

CENTRIFUGAL BEND MOMENTS; FAILURE RESISTANCE; MORTISE; TENON;

GAS TURBINES;

COMPRESSOR BLADE; FAILURE ANALYSIS; FATIGUE; GAS TURBINE;

EID: 0034579372     PISSN: 13506307     EISSN: None     Source Type: Journal    
DOI: 10.1016/S1350-6307(99)00045-X     Document Type: Article

References (4)

1. Stress analysis of first stage compressor blade and disk in a certain aeroengine (in Chinese)