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Failure analysis and damage development trend research of aero-engine high-pressure turbine blades

CAO Huiling1, CAO Pengshuang1, KANG Liping2, GU Ya'nan2   

  1. (1. College of Aeronautical Engineering, CAUC, Tianjin 300300, China; 2. Ameco, Beijing 100621, China)
  • Received:2016-10-28 Revised:2016-12-24 Online:2017-06-15 Published:2017-07-11

Abstract:

Datum about one airlines'CFM56-7B engine fleet containing borescope inspection information about high pressure turbine are used to analyze failure reasons of thermal barrier coatings. Statistical analyzing method is employed to determine the failure distribution model. Regression analysis is then conducted to obtain the damage development trend of leading edge of blade. Finally, average life expectancy of leading edge of blade is computed.

Key words: CFM56-7Bengine, high-pressure turbine blade, TBCs, failure analysis, damage development trend, average life

CLC Number: