System and method for in situ repair of turbine blades of gas turbine engines

Patent metadata

Field	Value
Publication number	US-10125611-B2
Application number	US-201615045812-A
Country	US
Kind code	B2
Filing date	Feb 17, 2016
Priority date	Feb 17, 2016
Publication date	Nov 13, 2018
Grant date	Nov 13, 2018

Abstract

The present disclosure is directed to an improved system and method for repairing a bend in a turbine blade of a turbine of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the turbine. The articulating guide includes a proximal end and a distal end. The system also includes a repair tool configured at the distal end of the articulating guide. Further, the repair tool is configured to fit over the turbine blade. Thus, the repair tool is configured to bend the turbine blade to an unbent position while the turbine blade is secured within the turbine.

First claim

What is claimed is:

1. A system for repairing a bend in a turbine blade of a turbine of a gas turbine engine, the system comprising:
an articulating guide configured to fit into an access port of the turbine, the articulating guide comprising a proximal end and a distal end; and
a repair tool configured at a distal end of the articulating guide, the repair tool comprising a first end having a through hole configured to slide over a blade tip of the turbine blade, the through hole comprising side walls that abut against the blade tip of the turbine blade so as to secure the repair tool to the blade tip, the repair tool further comprising a repair arm configured to apply force in a linear direction to bend the turbine blade to an unbent position while the turbine blade is secured within the turbine.

2. The system of claim 1 , wherein the bend is located in one of the blade tip, a leading edge, or a trailing edge of the turbine blade.

3. The system of claim 1 , further comprising a mounting component for securing a blade root of the turbine blade to a fixed location in the gas turbine engine.

4. The system of claim 3 , wherein the fixed location comprises a disk of the turbine.

5. The system of claim 2 , wherein the repair tool comprises at least one of a repair fixture or a repair clamp.

6. The system of claim 5 , wherein the repair fixture comprises a working head defining a first end and second end, the first end configured to slide over the blade tip of the turbine blade in a first direction, the second end configured with the articulating guide.

7. The system of claim 6 , wherein the working body further comprises a cavity configured to receive the blade tip through a slot thereof when the first end is slid over the blade tip.

8. The system of claim 5 , wherein the repair clamp further comprises a drive mechanism configured to drive the repair arm to bend the turbine blade to the unbent position.

9. The system of claim 8 , wherein the drive mechanism comprises at least one of an electrical drive mechanism, a hydraulic drive mechanism, or a pneumatic drive mechanism.

10. A method for repairing a bend in blade tip of a turbine blade of a gas turbine engine, the method comprising:
inserting an articulating guide into an access port of the turbine, the articulating guide having a repair tool at a distal end thereof, the repair tool having a first end having a through hole;
inserting a blade tip of the turbine blade into the through hole and sliding the first end of the repair tool over the blade tip so as to secure the repair tool to the blade tip, the through hole having side walls that abut against the blade tip of the turbine blade;
applying linear force, via a repair arm of the repair tool, at the bend of the turbine blade so as to bend the turbine blade back to an unbent position.

11. The method of claim 10 , further comprising securing a blade root of the turbine blade to a fixed location in the gas turbine engine, wherein the fixed location comprises a disk of the turbine.

12. The method of claim 11 , wherein the repair tool comprises a drive mechanism configured to drive the repair arm to bend the turbine blade to the unbent position.

13. The method of claim 12 , wherein the drive mechanism comprises at least one of an electrical drive mechanism, a hydraulic drive mechanism, or a pneumatic drive mechanism.

Assignees

• Gen Electric

Inventors

• Roberts Herbert Chidsey
• Diwinsky David Scott

Classifications

• F01D25/285

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• B21D1/06 Primary

  Removing local distortions · CPC title