Process for producing a TiAl guide vane ring for a gas turbine and a corresponding guide vane ring

Patent metadata

Field	Value
Publication number	US-9765632-B2
Application number	US-201313962005-A
Country	US
Kind code	B2
Filing date	Aug 8, 2013
Priority date	Aug 9, 2012
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising:
forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.

First claim

What is claimed is:

1. A process for producing a blade or vane ring segment for a gas turbine which comprises at least two adjacent main blade or vane parts having a single common blade or vane root, wherein the process comprises:
(a) forging at least two blanks made of a TiAl material,
(b) joining the blanks to form the blade or vane ring segment by an integral connection process, and
(c) remachining of a blank composite thus obtained by a material-removing process; (b) being carried out to result in a joining zone which extends through only a center or a central region of the common blade or vane root and each blank being formed as a cuboid with protruding joining zones.

2. The process of claim 1 , wherein the process further comprises carrying out one or more heat treatments between (b) and (c) or after (c).

3. The process of claim 1 , wherein (b) is effected by high-temperature soldering.

4. The process of claim 1 , wherein (b) is effected by high-temperature soldering using Ti-based or Ni-based solders.

5. The process of claim 1 , wherein (b) is effected by laser beam welding or electron beam welding.

6. The process of claim 5 , wherein during laser beam welding or electron beam welding the TiAl material is preheated above a brittle-ductile transition temperature of the TiAl material.

7. The process of claim 1 , wherein (b) is effected by high-temperature soldering carried out by local heating.

8. The process of claim 7 , wherein the local heating comprises inductive heating.

9. The process of claim 1 , wherein (b) is effected by friction welding.

10. The process of claim 9 , wherein the friction welding comprises linear friction welding.

11. The process of claim 9 , wherein the friction welding comprises orbital friction welding or multi-orbital friction welding.

Assignees

• MTU Aero Engines AG

Inventors

• Richter Karl-Hermann

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• B23P15/006

  turbine wheels · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• C22F1/183

  of titanium or alloys based thereon · CPC title