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<p>Based on a comprehensive microstructural investigation of an aero-engine turbine blade exhibiting shroud elongation after a 30-hour bench test, this study establishes overtemperature-induced softening and subsequent creep deformation as the primary failure mechanism. The service temperature field was reconstructed by correlating microstructural degradation patterns in failed regions with laboratory thermal exposure benchmarks, employing quantitative image analysis and comparative morphology assessment. Microstructural evidence revealed a distinct temperature gradient across the blade: severely deformed regions at the shroud leading edge (Sections A, B, C) and blade leading edge showed characteristic γ′ spheroidization, coarsening, and tertiary γ′ precipitation consistent with 1150-1200&#xa0;°C exposure. In contrast, shroud trailing-edge sections (C, D) and the blade trailing-edge retained cuboidal γ′ morphology with only γ channel widening, corresponding to 1100-1150&#xa0;°C. The blade pressure side remained below 1070&#xa0;°C. Critically, γ′ rafting orientations axial-perpendicular (N-type) near inner flow passages and axial-parallel (P-type) at serration tips-provided direct evidence of multiaxial stress states encountered in service. The study acknowledges limitations in laboratory benchmarks for replicating actual thermo-mechanical service conditions and in quantitative γ′ area fraction measurements due to overlapping values across temperature regimes. These constraints necessitated an integrated approach combining quantitative metrics with comprehensive qualitative assessment of morphological features—including the degree of cuboidal-to-spheroidal transformation, γ′ dissolution extent, and tertiary γ′ particle size distribution. This research demonstrates that integrated microstructural analysis serves as a powerful diagnostic tool for aero-engine failure investigation, with direct implications for maintenance strategy optimization and cooling system redesign in high-temperature turbine components.</p>

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Analysis of a Single-Crystal Blade Deformation and Failure

  • 期刊论文

  • 发表日期：

    2026年2月3日

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  • Zhen Zheng,
  • Xi Wang,
  • Quan Wang,
  • Mingping Zhou,
  • Changkui Liu,
  • Chunhu Tao,
  • Zheng Zhang

摘要

Based on a comprehensive microstructural investigation of an aero-engine turbine blade exhibiting shroud elongation after a 30-hour bench test, this study establishes overtemperature-induced softening and subsequent creep deformation as the primary failure mechanism. The service temperature field was reconstructed by correlating microstructural degradation patterns in failed regions with laboratory thermal exposure benchmarks, employing quantitative image analysis and comparative morphology assessment. Microstructural evidence revealed a distinct temperature gradient across the blade: severely deformed regions at the shroud leading edge (Sections A, B, C) and blade leading edge showed characteristic γ′ spheroidization, coarsening, and tertiary γ′ precipitation consistent with 1150-1200 °C exposure. In contrast, shroud trailing-edge sections (C, D) and the blade trailing-edge retained cuboidal γ′ morphology with only γ channel widening, corresponding to 1100-1150 °C. The blade pressure side remained below 1070 °C. Critically, γ′ rafting orientations axial-perpendicular (N-type) near inner flow passages and axial-parallel (P-type) at serration tips-provided direct evidence of multiaxial stress states encountered in service. The study acknowledges limitations in laboratory benchmarks for replicating actual thermo-mechanical service conditions and in quantitative γ′ area fraction measurements due to overlapping values across temperature regimes. These constraints necessitated an integrated approach combining quantitative metrics with comprehensive qualitative assessment of morphological features—including the degree of cuboidal-to-spheroidal transformation, γ′ dissolution extent, and tertiary γ′ particle size distribution. This research demonstrates that integrated microstructural analysis serves as a powerful diagnostic tool for aero-engine failure investigation, with direct implications for maintenance strategy optimization and cooling system redesign in high-temperature turbine components.