Damping inlay for turbine blades

Patent metadata

Field	Value
Publication number	US-10041359-B2
Application number	US-201514932313-A
Country	US
Kind code	B2
Filing date	Nov 4, 2015
Priority date	Nov 10, 2014
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

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.

First claim

The invention claimed is:

1. 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. The turbine blade according to claim 1 , wherein the damping material comprises one or more of a mass damper, a mass, a wire mesh, a powder, particles, or a liquid.

3. The turbine blade according to claim 1 , wherein a plurality of damping inlays are provided for reduction of a plurality of damping modes.

4. A gas turbine comprising at least one turbine blade according to claim 1 .

5. The turbine blade according to claim 1 , wherein the damping inlay is made of a nickel based super alloy.

6. The turbine blade according to claim 1 , wherein the damping inlay is a substantially cuboid shape with a curvature on an outer face to follow a curvature of the blade.

7. The turbine blade according to claim 1 , wherein the blade is a hollow blade having a leading edge, a trailing edge, a pressure side, a suction side and a web, and wherein the damping inlay is provided at an intersection where the web meets the side wall.

8. The turbine blade according to claim 1 , wherein the damping material is a spherical mass.

9. The turbine blade according to claim 1 , wherein the damping material is a mass damper comprising a mass and a spring.

10. The turbine blade according to claim 1 , wherein the damping inlay is disposed in the side wall of a hollow turbine blade.

11. A method of making a turbine blade comprising:
manufacturing a turbine blade, the turbine blade having a side wall with an outer surface and a recess within the outer surface; and
providing a damping inlay 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 and being 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.

12. The method of claim 11 , wherein the manufacturing of the turbine blade comprises the manufacturing of the turbine blade and removing a portion of the outer surface of the turbine blade to create the recess in the outer surface.

13. The method of claim 12 , wherein the portion of the outer surface of the turbine blade is removed using eroding, grinding or milling.

14. The method of claim 11 , wherein the providing of the damping inlay comprises:
manufacturing the damping inlay and attaching the damping inlay within the recess.

15. The method of claim 11 , wherein the providing of the damping inlay comprises:
at least partially filling the recess with a damping material and covering the recess to complete the damping inlay.

16. The method of claim 11 , wherein the damping inlay is attached to the turbine blade using welding, brazing, soldering, selective laser melting, or glue.

17. The method of claim 11 , wherein the damping inlay is manufactured, at least in part, by laser melting, welding, forging or casting.

18. A method of making a turbine blade comprising:
manufacturing a turbine blade, the turbine blade having a surface and a recess in the surface; and
providing a damping inlay 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, wherein the turbine blade is manufactured by casting, and the damping inlay is attached to the turbine blade during casting of the turbine blade.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Brandl Herbert
• Beretta-Müller Arrigo

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2220/30

  in turbines · CPC title

• F01D5/26 Primary

  Antivibration means not restricted to blade form or construction or to blade-to-blade connections {or to the use of particular materials} · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title