US 10,041,359 B2 · Damping inlay for turbine blades

Abstract

The invention concerns a turbine blade comprising a surface, a recess within the surface, and a damping inlay within the recess. The damping inlay comprises a chamber with a damping material, for example particles. The damping inlay should substantially maintain the aerodynamic profile of the blade to enable normal operation. A further embodiment of the invention describes the method of manufacture of a turbine blade with a damping inlay. The method comprises the steps of manufacturing a turbine blade having a surface and a recess in the surface, and providing one or more damping inlays within the recess such that the damping inlay substantially maintains the aerodynamic profile of the blade, the damping inlay comprising a chamber and a damping material disposed within the chamber.

Claims18

Dependent claims

A turbine blade comprising:

a side wall with an outer surface;
a recess within the outer surface;
a damping inlay within the recess, wherein the damping inlay comprises a chamber and a damping material disposed within the chamber, and the damping inlay substantially maintains the aerodynamic profile of the blade and is disposed in the side wall of the turbine blade;
and
a cooling means, wherein at least part of the cooling means is provided upstream of the damping inlay and includes at least one film cooling hole in the side wall of the turbine blade.

2 more elements

Dependencies are inferred from the claim text.

Damping inlay for turbine blades

Life of this patent

Damping inlay for turbine blades

Life of this patent

Abstract

Claims18