Reason for Cracking of Straightener Blades of Compressor

LIU Liyu; LI Jiajia; JIANG Tao; HE Jin; TAO Chunhu

doi:10.11973/jxgccl201902016

Materials and Mechanical Engineering > 2019 > 43(2): 78-81. > DOI: 10.11973/jxgccl201902016

LIU Liyu, LI Jiajia, JIANG Tao, HE Jin, TAO Chunhu. Reason for Cracking of Straightener Blades of Compressor[J]. Materials and Mechanical Engineering, 2019, 43(2): 78-81. DOI: 10.11973/jxgccl201902016

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Reason for Cracking of Straightener Blades of Compressor

1. Failure Analysis Center of Aviation Industry Corporation of China, Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation, Aviation Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China;
2. AECC Gas Turbine Research Establishment, Chengdu 610500, China

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Received Date: September 26, 2017
Revised Date: September 11, 2018

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After in-plant testing for 20 h, the straightener blades of the compressor in a certain type of aero engine showed longitudinal cracks in the middle of blade body. Appearance inspection, microstructure and fracture morphology observation and hardness testing were conducted on the cracked blades. The blade vibration at the working speed of the aero engine was studied and the formation cause of cracks was discussed. The results show that the crack mode of the straightening blade was high-cycle fatigue cracking. The cracks formed by rotating bending resonance caused by rear rotor in the working speed range of the engine. By adoption of frequency modulation scheme of thickening the whole blade, adjusting the speed at which the rear rotor blade stirred up the rotating bending resonance to above the maximum engine working speed, the crack formation of the compressor straightener blade could be prevented.
- straightener blade,
- longitudinal crack,
- high-cycle fatigue,
- rotating bending resonance

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