US 8,708,682 B2Granted

Repair method

AssigneeMTU Aero Engines AG

InventorsRoland Huttner, Karl-Heinz Dusel, Erwin Bayer, Albin Platz

Life of this patent

Estimating the term…

Loading patent…

Abstract

A method for repairing gas turbine components, in particular gas turbine blades, including at least the following steps: a) preparing a gas turbine component to be repaired; b) removing a damaged portion from the gas turbine component to be repaired, thereby forming a plane separation surface; c) placing the gas turbine component at least partly in a process chamber in such a way that the plane separation surface extends approximately horizontally within the process chamber; d) filling the process chamber with a metal powder that is bonding-compatible with the material of the gas turbine component to be repaired, namely up to the level of the separation surface; e) building up the removed portion on the separation surface by depositing metal powder in layers onto the separation surface and by fusing the metal powder, which has been deposited in layers onto the separation surface, to the separation surface.

Claims4

Dependent claims

A process chamber for repairing a gas turbine component, which, following removal of a damaged portion, has a binding portion having a plane separation surface, the removed portion being built up anew by the deposition in layers of metal powder onto the separation surface and by the fusing together of the metal powder and the separation surface, the process chamber comprising:

a receiving space;
an infeed opening connected to the receiving space, the infeed opening configured and arranged to introduce into the receiving space a first portion of the binding portion, the first portion having the separation surface, a second portion of the binding portion remaining in the infeed opening;
a sealing device located in the infeed opening, sealing a seal between the second portion of the binding portion and the infeed opening;
and
a movable slide projecting into the receiving space and movable in parallel to the separation surface to even out metal powder deposited on the separation surface and provide a defined, uniform metal powder layer on the separation surface prior to the fusing together of the metal powder with the material of the gas turbine component to be repaired.

2 more elements

Dependencies are inferred from the claim text.

Facts

Application: 12/998,560Filed 5 Nov 2009
Priority: DE 10 2008 056 3367 Nov 2008
Published: US 2011/0217457 A18 Sep 2011
Granted: 29 Apr 2014
Term ends: Not estimatedThe source records don’t support an estimate.

Classification17 codes

B22F 7/062
Of composite workpieces or articles from parts, e.g. to form tipped tools: involving the connection or repairing of preformed parts
B22F 10/28
Direct sintering or melting: powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
B23P 6/007
Repairing turbine components, e.g. moving or stationary blades, rotors,: using only additive methods, e.g. build-up welding
F01D 5/005
Blades; Blade-carrying members ; Heating, heat-insulating, cooling or antivibration means on the blades or the members: repairing methods or devices