US 7,882,639 B2Granted

Braze repair of shroud block seal teeth in a gas turbine engine

AssigneeGeneral Electric Company

InventorJohn Matthew Powers

Life of this patent

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Abstract

An undersize repair region of a gas turbine engine stationary shroud is repaired with a sufficient mass of a repair material. The repair region includes a protruding portion that is undersized, and the repair includes machining of the protruding portion, grooving the resulting rub surface, inserting a replacement element, applying a brazing repair material, and brazing the article to form a repaired article. The repair material preferably includes a first fraction of a first powder of a first alloy component, and a second fraction of a second powder of a second alloy component. The first alloy component and the second alloy component have different solidus temperatures. The repair material is placed in the repair region. The repair material and the repair region are heated to melt the repair material but not the repair region, and thereafter the repair material and the repair region are cooled to solidify the repair material.

Claims18

Dependent claims

A gas turbine engine stationary shroud repaired according to the method comprising the steps of:

providing the gas turbine engine stationary shroud having an undersize repair region made of a shroud material, wherein the repair region is a protruding element located on a gas flow path surface of the gas turbine engine stationary shroud;
repairing the repair region of the gas turbine engine stationary shroud so that the repair region is no longer undersize, further including the steps of:
removing the protruding element from the shroud;
forming a receiving groove in the repair region, the groove extending below the gas flow path surface;
placing a replacement element into the receiving groove;
placing a braze repair material in the repair region, the braze repair material having a solidus temperature less than that of the shroud material;
heating the repair region, the replacement element, and the repair material to a brazing temperature sufficient to melt at least a portion of the braze repair material but not the replacement element or shroud material of the repair region, so that the repair material flows over the repair region, into the groove, contacting the replacement element and the gas flow surface;
and thereafter
cooling the melted braze repair material and the repair region to solidify the braze repair material;
wherein the step of placing a repair material in the repair region includes placing the repair material in the receiving groove.

7 more elements

Dependencies are inferred from the claim text.

Facts

Application: 12/048,672Filed 14 Mar 2008 · division
Priority: 14 Jun 2004
Published: US 2008/0209726 A14 Sep 2008
Granted: 8 Feb 2011
Term ends: Not estimatedThe source records don’t support an estimate.

Classification20 codes

B23P 6/005
Repairing turbine components, e.g. moving or stationary blades, rotors,: using only replacement pieces of a particular form
B23K 1/0018
Specially adapted for particular articles or work: brazing of turbine parts
B23P 6/002
Restoring or reconditioning objects: repairing turbine components, e.g. moving or stationary blades, rotors,
F01D 5/005
Blades; Blade-carrying members ; Heating, heat-insulating, cooling or antivibration means on the blades or the members: repairing methods or devices

Family

Application10/869,344Parent of this division · filed 14 Jun 2004
US 2008/0209726 A1Pre-grant publication · published 4 Sep 2008
US 7,363,707 B2Parent of this division
US 2005/0274009 A1Published application
US 7,882,639 B2This patent

From the US filing history. Foreign family members aren’t listed.