US 10,519,783 B2Granted

Method for modifying a shroud and blade

AssigneeGeneral Electric Company

InventorsRichard Gordon Rollings, Kevin Leon Bruce, William Scott Zemitis

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Abstract

A method for modifying an airfoil shroud located at a tip of an airfoil is provided. A locating step locates a reference location in a first end edge. The reference location includes a portion of a fillet. A seal rail extends circumferentially along a radially outer surface of the airfoil shroud. The fillet extends along the radially outer surface and is positioned directly adjacent to the seal rail. A forming step forms a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location. The compound relief cut has a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge. Modifying the airfoil shroud is complete following forming the compound relief cut.

Claims17

Dependent claims

A method for modifying an airfoil shroud located at a tip of an airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge, the method comprising:

locating a reference location in the first end edge of the airfoil shroud, the reference location including a portion of a fillet, a seal rail extending circumferentially along a radially outer surface of the airfoil shroud, the fillet extending along the radially outer surface and positioned directly adjacent to the seal rail;
forming a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location, the compound relief cut having a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge, the second radius being larger than the first radius, wherein modifying the airfoil shroud is complete following forming the compound relief cut,
wherein an exterior angle formed between an end of the second cut and the first end edge is a reflex angle.

Dependencies are inferred from the claim text.

Facts

Application: 15/387,975Filed 22 Dec 2016
Published: US 2018/0230817 A116 Aug 2018
Granted: 31 Dec 2019
Term ends: Not estimatedThe source records don’t support an estimate.

Classification11 codes

F01D 5/225
Blade-to-blade connections, e.g. for damping vibrations: by shrouding
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
F05D 2230/10
Manufacture: by removing material