| Citation: | ZHAO Yan, CHEN Ruoqi, SHEN Tianbao, et al. Remaining life prediction method for aero-engine turbine blades oriented to on-condition maintenance[J]. Journal of Aerospace Power, 2025, 40（8）：20240532 doi: 10.13224/j.cnki.jasp.20240532
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A framework for calculating the life consumption of aero-engine turbine blades oriented to on-condition maintenance was proposed. An engine system performance model based on the long-/short-term memory network was established, and the fast calculation of the turbine blade thermal simulation model instream flow cross-section parameters based on the measured flight reference was achieved. A fast mapping method of turbine blade temperature/stress field based on the reduced-order model was presented. Furthermore, the load information of the dangerous parts of the turbine blade were extracted, and the high-precision remaining life prediction of the turbine blade was implemented. Compared with the traditional simulation methods, the maximum relative error of the proposed airflow cross-section parameter model calculation results did not exceed 5%. The proposed fast temperature/stress field mapping algorithm calculated the temperature field root mean square error within ±5 K and the stress field root mean square error within ±3 MPa, and the computation speed was improved by more than 99%. The high accuracy and high efficiency of the turbine blade load state assessment and remaining life calculation in a flight cycle were achieved.
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