Method for detuning the blades in a gas turbine engine and corresponding gas turbine engine.

摘要

The gas turbine has airfoils (10,12) which are arranged alternately in the circumferential direction. The airfoils are provided with arrays of cavities (21A,21B). The second array of cavities (21B) is different from first array of cavities (21A). The airfoils are provided as rotor blades or stator vanes. The arrays of cavities are provided with different numbers of cavities and similar volume. The airfoils are joined together by material-to-material bond (30). An independent claim is included for a method for manufacturing the gas turbine.