Turbine blade comprising a cavity with wall surface discontinuities and process for the production thereof

Patent metadata

Field	Value
Publication number	US-11168566-B2
Application number	US-201615368907-A
Country	US
Kind code	B2
Filing date	Dec 5, 2016
Priority date	Dec 5, 2016
Publication date	Nov 9, 2021
Grant date	Nov 9, 2021

Abstract

The invention relates to a turbine blade which comprises at least one cavity that is defined by a wall with one or more surface discontinuities which preferably are selected from elevations, depressions and undercuts and preferably change at least one eigenmode of the blade. The blade may suitably be produced by a generative production method such as selective laser melting (SLM).

First claim

The invention claimed is:

1. A turbine blade which comprises at least one cavity, wherein the at least one cavity is defined by a wall having one or more surface discontinuities which comprise at least one elevation, a maximum height of the at least one elevation being at least twice a wall thickness in an area immediately adjacent to the at least one elevation and/or the maximum height of the at least one elevation being at least twice a minimum wall thickness of the blade.

2. The turbine blade of claim 1 , wherein the maximum height of the at least one elevation is at least twice the wall thickness in an area immediately adjacent to the at least one elevation.

3. The turbine blade of claim 1 , wherein the maximum height of the at least one elevation is at least twice the minimum wall thickness of the blade.

4. The turbine blade of claim 1 , wherein two elevations on opposite sides of the wall are in contact with each other.

5. The turbine blade of claim 1 , wherein the turbine blade is a guide vane of a gas turbine.

6. The turbine blade of claim 1 , wherein the turbine blade is a rotating blade of a gas turbine.

7. The turbine blade of claim 1 , wherein at least one of the one or more surface discontinuities changes at least one eigenmode of the blade compared to a blade without the at least one surface discontinuity.

8. The turbine blade of claim 1 , wherein the turbine blade comprises a blade root and a blade leaf and at least the blade leaf is produced by a generative production method.

9. The turbine blade of claim 8 , wherein the generative production method comprises selective laser melting (SLM).

10. The turbine blade of claim 1 , wherein at least a part of the blade is made from a Ti alloy.

11. The turbine blade of claim 10 , wherein the Ti alloy is or comprises a TiAl alloy.

12. The turbine blade of claim 1 , wherein at least a part of the blade is made from a Ni-base alloy.

13. A turbine, wherein the turbine comprises the turbine blade of claim 1 .

14. A blade arrangement of a turbine, wherein the blade arrangement comprises the turbine blade of claim 1 .

15. The blade arrangement of claim 14 , wherein the blade arrangement comprises two adjacent blades each of which comprises at least one cavity which is defined by a wall with one or more surface discontinuities, which blades differ only in that the one or more surface discontinuities of their cavity walls are different to thereby provide adjacent blades with different eigenmodes.

16. The turbine blade of claim 1 , wherein two elevations on opposite sides of the wall are combined to form a web or bridge inside the cavity.

17. The turbine blade of claim 1 , wherein the one or more surface discontinuities further comprise at least one depression.

18. The turbine blade of claim 1 , wherein the one or more surface discontinuities further comprise at least one undercut.

19. A turbine blade which comprises at least one cavity, wherein the at least one cavity is defined by a wall having one or more surface discontinuities which comprise at least one depression.

20. A process for making the turbine blade of claim 1 , wherein the process comprises building up at least a part of the blade that comprises the at least one cavity by a generative production method which includes forming the one or more surface discontinuities.

Assignees

• MTU Aero Engines AG

Inventors

• Kraus Juergen
• Klingels Hermann
• Feldmann Manfred

Classifications

• F05D2240/126

  Baffles or ribs · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2300/174

  Titanium alloys, e.g. TiAl · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title