Failure analysis of J85-CAN-15 turbojet engine compressor disc

被引：6

作者：

Saracyakupoglu, Tamer ^{[1
]}

机构：

[1] Istanbul Gelisim Univ, Dept Aeronaut Engn, TR-34315 Istanbul, Turkey

来源：

ENGINEERING FAILURE ANALYSIS | 2021年 / 119卷

关键词：

J85-CAN-15; Dovetail post; Fatigue failure; Crack; Manufacturing defect;

D O I：

10.1016/j.engfailanal.2020.104975

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

This paper analyzes the J85-CAN-15 engine damage due to fracture of the compressor disc 8th stage dovetail post. An Inner Object Damage (IOD) phenomenon was identified. The damaged compressor disc material is Incoloy 901 forging. The composition of the disc is determined as 42.7%-Ni, 34%-Fe, 13.5%-Cr, 6.2% Mo, 2.5%Ti, 0.1%-Cu, and 0.05%-C. The average hardness value of the material is 44 HRC. The burrs have been observed under Field Emission Scanning Electron Microscope (SEM) and they are considered as the origin of the fatigue on the engine compressor disc. The metallurgical analysis results show that manufacturing defect was propagated under the repeated low and high cyclic loads.

引用

页数：8

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