摘要
Hollow superalloy or single-crystal superalloy turbine blades are the most important component of advanced aeroengines for fifth-and higher-generation fighter aircrafts [1,2,3]. The thrust-toweight ratio is largely influenced by the turbine inlet temperature,which places strict requirements on the performance of the turbine blades at high operating temperatures [4]. To reduce the operating temperature of the blades, complex internal cooling structures are required. However, the fabrication of complex cooling channels inside the blades is an unquestionably challenging task [5].
基金
the National Science and Technology Major Project,China(2017-Ⅵ-0002-0072)(Y2019-Ⅶ-0011-0151)
the National Key Research and Development Program,China(No.2018YFB1106600)。