Method for producing a run-in coating, a run-in system, a turbomachine, as well as a guide vane

Patent metadata

Field	Value
Publication number	US-9840919-B2
Application number	US-201214233663-A
Country	US
Kind code	B2
Filing date	Jul 18, 2012
Priority date	Jul 20, 2011
Publication date	Dec 12, 2017
Grant date	Dec 12, 2017

Abstract

A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating.

First claim

What is claimed is:

1. A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, comprising:
forming the run-in coating as an integral blade portion during a generative manufacture of a blade, wherein the generative manufacture includes forming the blade and the run-in coating through deposition and melting of metal powder in layers.

2. The method as recited in claim 1 further comprising constructing a generative structure during manufacture of the blade and removing the structure following the manufacture of the blade.

3. The method of claim 1 , wherein the run-in coating forms an abradable ring, and the abradable ring includes a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps which together form an integral, closed or open abradable ring having a chamber-type material structure.

4. The method of claim 1 , wherein each run-in coating includes a damping layer for shock absorption and a braking layer for optimizing braking.

5. A run-in system comprising an integral, closed or open abradable ring including a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps along the circumference of the abradable ring, the run-in coatings forming the abradable ring extending over a rotor blade row and located axially between outer shrouds of the rotor blade row and outer shrouds of a guide vane row and having a chamber-type material structure.

6. The run-in system as recited in claim 5 wherein the abradable ring is formed either on a side of the outer shrouds of the rotor blade row opposite a side of the outer shrouds of the guide vane row, or on a side of the outer shroud of the guide blade row opposite a side of the outer shroud of the rotor vane row.

7. The run-in system as recited in claim 5 wherein the abradable ring is placeable on leading sides of outer shrouds of the guide vane row.

8. The run-in system as recited in claim 5 wherein the abradable ring is placeable on leading edges of guide vanes.

9. The run-in system as recited in claim 5 wherein an abrasive ring is configurable for running onto the abradable ring of trailing sides of outer shrouds of the rotor blade row in response to a shaft breakage.

10. The run-in system as recited in claim 5 wherein the run-in coatings are manufactured in accordance with the method recited in claim 1 .

11. A turbomachine comprising the run-in system as recited in claim 5 , and an abrasive ring for running onto the abradable ring in response to a shaft breakage,
the abradable ring being disposed in the leading region of the guide vane row, and the abrasive ring being formed in the upstream trailing region of a rotor blade row opposite the abradable ring.

12. A guide vane row comprising
a plurality of guide vanes, each guide vane including an outer shroud and an inner shroud; and
an abradable ring in a leading region of the guide vane, wherein the abradable ring includes a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps along the circumference of the abradable ring, the plurality of run-in coatings having a chamber-type material structure.

13. The guide vane as recited in claim 12 wherein the run-in coatings are formed on a leading side of the outer shrouds.

14. The guide vane as recited in claim 12 wherein the run-in coatings are formed radially outwardly on a leading edge of a blades of each guide vane.

15. The guide vane as recited in claim 12 wherein the run-in coatings are formed on an edge portion of a leading edge displaced upstream relative to a radially inner edge portion of each guide vane.

Assignees

• Bayer Erwin
• Hess Thomas
• Hiller Sven-J
• Geiger Peter
• MTU Aero Engines AG

Inventors

• Bayer Erwin
• Hess Thomas
• Hiller Sven-J
• Geiger Peter

Classifications

• Y10T29/49316

  Impeller making · CPC title

• F01D5/288 Primary

  Protective coatings for blades · CPC title

• F01D21/04

  responsive to undesired position of rotor relative to stator {or to breaking-off of a part of the rotor}, e.g. indicating such position · CPC title

• F01D21/006 Primary

  Arrangements of brakes (brakes per se F16D) · CPC title