COMPOSITE TURBINE BLADE FOR HIGH-TEMPERATURE APPLICATIONS

摘要

The present invention relates to a composite turbine blade (10) for high temperature applications such as gas turbines or the like having a root (1) for mounting a blade (10) in a corresponding circumferential assembly groove of a rotor and an airfoil (2) connected to the root (1). An inner carrying structure (3) is provided to extend over at least a portion of the root (1) as well as at least a portion of the airfoil (2), wherein the inner carrying structure (3) is made of a high strength eutectic ceramic and the airfoil (2) is made of a ceramic matrix composite (CMC) material.