To address the challenge of quantitatively evaluating the structural reliability of probe in high-temperature flow fields of aero-engines under multi-load coupling effects, a fatigue-creep coupled failure analysis method was developed specifically for this probe. Based on the one-way fluid-thermal-solid coupling method, the structural strength of the probe was evaluated. The results indicated a maximum temperature of approximately 850℃, a maximum static stress of 209.4 MPa, and a maximum random vibration stress of 44.6 MPa. The Basquin equation combined with the Goodman correction model was applied to assess high-cycle fatigue damage, yielding a fatigue cycle number of 1.23×1018. The Larson-Miller equation was utilized to calculate a creep cycle number of 1.03×109. By employing the linear cumulative damage model, the service life under the coupling of multiple damage mechanisms was analyzed. It was determined that with a safety factor of 2, the service life is ≥472.1 h, meeting the design requirements. In-engine verification demonstrates that the probe has safely operated for over 50 h. This method enables the quantitative assessment of high-temperature probe failure, providing a technical foundation for the future design of high-temperature probe in aero-engines.