Gas Turbine Cooling Plate Optimization Design For Small And Median Size Aeroengine

Gas turbine cooling plate forming passage for blade cooling,constraining axial displacement of blades and sealing high temperature gas plays important roles for small and median size aero-engine.The static and alternative loads for cooling plate are of complexity and the strength and life of cooling plate are directly related to safety of the engine.Present paper targets a developing turboshaft engine whose cooling plate of gas turbine cannot meet the strength and life requirements and then the structure of this plate is optimized and also verified by tests.The strength analysis,life estimation and optimization algorithms are researched during the optimization process.The burst speed methods are examined and results prove that the modified mean stress method can meet the requirements of efficiency and precision simultaneously.The life prediction methods are investigated and results suggest that the Walker method is an effective and reliable approach.Algorithms for cooling plate optimization are researched and then a hybrid optimization algorithm involving Random Test Method and Sequential Quadratic Programming is presented for the typical features of cooling plates.The example shows that current algorithm can enhance the optimization efficiency obviously.Based on the research above,the cooling plate optimization work for this engine has completed and test suggests that its strength and life can satisfy the designing criterion.Present paper has analyzed and investigated the cooling plate from the perspective of strength analysis,life estimation,structure optimization and test verification,and then a relative integrated and effective methodology for strength,life and optimization for cove plate has developed which is valuable for both theoretic perspective and engineering application,and can support the structure design for complicated cooling plate for gas turbine engine.