The fracture and shedding of turbine blades in aero-engine systems are intimately linked to blade temperature. The precise measurement of turbine blade temperature is significant for ensuring the safe operation of aero-engines. However, traditional infrared radiation temperature measurement methods often face challenges in maintaining accuracy due to factors such as the nonuniform emissivity of turbine blade materials, pronounced reflections from high-temperature objects in the surroundings, and variations in detection angles. To address these issues, this article leverages the principles of radiation transfer theory and infrared thermal imaging temperature measurement to analyze the key factors that influence temperature measurement results. A modified model for infrared radiation temperature measurement of three-dimensional curved surfaces under complex backgrounds is formulated. To obtain the necessary parameters for the temperature correction model, the experimental measurement is designed to determine crucial factors such as emissivity, bidirectional reflection distribution function, and angle coefficient for the curved surface. By applying the temperature correction model proposed in this study, the infrared-corrected temperature values for the curved surface are derived. Comparative analysis of these results with temperature measurements obtained from thermocouples positioned at representative locations demonstrates a reduction in temperature measurement error from approximately 4% prior to correction to less than 1% . This result substantiates the high accuracy and adaptability of the proposed correction model, underscoring its potential to provide valuable support for enhancing aerodynamic heat transfer test technology and facilitating the development of major aero-engine equipment, particularly turbine blades.