Current research on corrosion damage of aero-engine turbine blades is increasingly diverse, yet the methodologies and data formats lack unified evaluation criteria. Existing studies include salt-coated hot corrosion tests on material specimens, gas thermal corrosion experiments on specimens and components following HB7740-2004 “Gas Thermal Corrosion Test Method”, full-engine corrosion susceptibility bench tests, and field data on hot corrosion fatigue of turbine blades induced by flight environments. It is recommended to sample and analyze deposits from corroded areas of field-returned turbine blades using energy spectrum analysis to establish a deposit composition database. Additionally, atmospheric and sand/dust compositions from various field envi-ronments should be analyzed to compile a statistical table of field environmental spectra. A systematic consolidation of diverse corrosion data and supplementary experimental studies are required to develop conversion criteria between different research datasets based on the equivalent damage principle.