Integrated turbine bladed disk made of ceramic-matrix composite

The invention relates to an integrated turbine bladed disk made of a ceramic-matrix composite. The integrated turbine bladed disk is made of the carbon-fiber-reinforced pyrolytic carbon-silicon carbide (C/C-SiC) ceramic-matrix composite; matrix materials of the C/C-SiC ceramic-matrix composite are pyrolytic carbon and silicon carbide; and fiber materials are carbon fibers. According to the integrated turbine bladed disk, the maximum carrying capacity of the integrated turbine bladed disk is remarkably improved, and meanwhile, the high-temperature resistance and the cycle life of the integrated turbine bladed disk are increased, so that the integrated turbine bladed disk can better meet requirements of engines, particularly, high-performance aviation engines. 本发明涉及种陶瓷基复合材料整体涡轮叶盘，所述整体涡轮叶盘由碳纤维增强热解碳-碳化硅(C/C-SiC)陶瓷基复合材料制成；其中，所述碳纤维增强热解碳-碳化硅陶瓷基复合材料的基体材料为热解碳和碳化硅，纤维材料选用碳纤维。本发明提供的陶瓷基复合材料整体涡轮叶盘，显著提高了整体涡轮叶盘的最大承载能力，同时提高了其耐高温性和循环寿命，从而使其能够更好的满足发动机尤其是高性能航空发动机的需求。