The damage of the volute vane in a particle separator caused by foreign object impact is studied in order to increase its ability of resisting foreign object damage and to reduce the influence of foreign object to the safe run of an aero-turbo-shaft engine.

Parametric design of turbine blades based on feature modeling;

Research on Fatigue Life of Large Gas Turbine Blades;

The single crystal Ni-base superalloys were widely used for manufacturing advance gas turbine blades,but the ignored weakness of these alloys to date is that the extent of primary creep at intermediate temperature is much higher than that at high temperature.

Error Analysis on Turbine Blade;

Displacement transfer with the mesh deformation method in multidisciplinary optimization of turbine blades;

Turbine blade design and optimization based on the combination means of parametric-Bezier curve;

Research and Application of Parting Design for Turbo Blade Mould with the Case- based Reasoning (CBR);

An integration system is set up to meet the need for information integration in the process of mold design and manufacture and detection of aero-engine turbo blade by investment casting.

Seven stageⅠturbo blades fractured during working time of an engine.

Experimental study on bird damage of vortex vane in the particle separator;

Precise reconstruction technology of curved surface of turbine vane;

The third class turbine vanes of some engine have fractured three times successively.

Therefore, eliminating these grain boundries can improve the resistance of turbine vane cracks, based on which directly solidification was developed.