BLADE OF A GAS TURBINE ENGINE FOR AN AIRPLANE, AND A METHOD FOR MANUFACTURING THE SAME

摘要

A gas turbine engine blade for aircraft which has a 3-dimensional blade surface shape twisted around a center line at an angle of 45 degrees or more and 70 degrees or less, wherein the aforementioned blade is provided with multiple composite material prepregs which contain reinforced fiber and which are integrally molded after being laminated in the thickness direction, and the aforementioned reinforced fiber runs continuously without interruption within each layer of the aforementioned composite material prepregs.