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

Patent metadata

Field	Value
Publication number	US-2018156037-A1
Application number	US-201615368907-A
Country	US
Kind code	A1
Filing date	Dec 5, 2016
Priority date	Dec 5, 2016
Publication date	Jun 7, 2018
Grant date	—

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 preferably selected from elevations, depressions and undercuts. The blade may suitably be produced by a generative production method.

First claim

1 . A turbine blade which comprises at least one cavity, wherein that the at least one cavity is defined by a wall with one or more surface discontinuities.

2 . The turbine blade of claim 1 , where the one or more surface discontinuities are selected from elevations, depressions and undercuts.

3 . The turbine blade of claim 2 , wherein the one or more surface discontinuities comprise one or more elevations.

4 . The turbine blade of claim 3 , wherein the maximum height of at least one elevation is at least twice a wall thickness in an area immediately adjacent to an elevation.

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

6 . The turbine blade of claim 3 , wherein two elevations on opposite sides of a wall are in contact with each other and/or together are combined to form a web or bridge inside the cavity.

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

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

9 . 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.

10 . 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.

11 . The turbine blade of claim 10 , wherein the generative production method comprises selective laser melting (SLM).

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

13 . The turbine blade of claim 12 , wherein the Ti alloy is or comprises a TiAl alloy.

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

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

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

17 . The blade arrangement of claim 16 , 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.

18 . A process for making a turbine blade comprising at least one cavity, 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 one or more surface discontinuities.

19 . The process of claim 18 , wherein the one or more surface discontinuities are selected from elevations, depressions and undercuts in a surface of a wall which defines the at least one cavity.

20 . A turbine blade which is obtained by the process of claim 19 .

Assignees

• MTU Aero Engines AG

Inventors

• Kraus Juergen
• Klingels Hermann
• Feldmann Manfred

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F05D2230/31

  Layer deposition · CPC title

• F05D2240/126

  Baffles or ribs · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title