Method of extending life of rotating parts

Patent metadata

Field	Value
Publication number	US-8959767-B2
Application number	US-201213683302-A
Country	US
Kind code	B2
Filing date	Nov 21, 2012
Priority date	Nov 21, 2012
Publication date	Feb 24, 2015
Grant date	Feb 24, 2015

Abstract

A method of refurbishing a gas turbine engine rotor is disclosed and includes an initial step of inspecting a rotor for defects such as cracks. A strain is then generated around any detected cracks in the rotor to create enhanced plasticized zones about the detected defects that delay defect propagation. Strain is generated by rotating the rotor at speeds greater than operational speeds to induce the desired strain and delay the propagation of defects.

First claim

The invention claimed is:

1. A method of extending operational life of a gas turbine engine rotor comprising the steps of:
inspecting a rotor for defects; and
generating an enhanced compressive residual stress around any defects in the rotor to create plasticized zones about the defects that delay defect propagation by rotating the rotor at a predetermined temperature at a speed above a normal operational speed for generating the plasticized zones around the defects.

2. The method as recited in claim 1 , wherein the rotating speed of the rotor greater than about 30% above a normal operating speed.

3. The method as recited in claim 1 , wherein the rotating speed of the rotor is between about 5% and 45% above a normal operational speed.

4. The method as recited in claim 1 , wherein the rotating speed of the rotor is between about 25% and 35% above a normal operational speed.

5. The method as recited in claim 1 , including rotating the rotor for a time representative of a flight cycle.

6. The method as recited in claim 1 , including maintaining the predetermined temperature within the range replicating operational temperatures of the rotor during rotation of the rotor.

7. The method as recited in claim 1 , including heating the rotor to a temperature within a range between 70° F. and 1250° F.

8. The method as recited in claim 1 , including placing blades and/or representations of blades onto the rotor during rotation of the rotor.

9. The method as recited in claim 1 , wherein the rotor comprises one of a compressor rotor and a turbine rotor.

10. The method as recited in claim 1 , including evaluating the defect in view of a predefined criteria and conducting rotor refurbishment when the defects within the rotor meet the criteria.

11. The method as recited in claim 1 , including inspecting the rotor after creation of the plasticized zones to confirm that the defects fall within desired operational criteria.

12. A method of retarding defect growth in a rotor comprising:
spinning the rotor at an over-speed between of at least 30% above a normal operational speed;
cycling the rotor between a normal operational speed and the over-speed for a duration of time representative of a flight cycle; and
generating a plasticized zones about a defect by spinning the rotor at the over-speed.

13. The method as recited in claim 12 , wherein the rotor comprises one of a turbine rotor and a compressor rotor.

Assignees

• United Technologies Corp
• Georgia Inst Technology

Inventors

• Staroselsky Alexander
• Pietraszkiewicz Edward F
• Mongillo Jr Dominic J
• Barker Vincent
• Adair Benjamin
• Johnson W Steven

Classifications

• F05D2270/11

  to prolong engine life · CPC title

• F05D2300/60

  Properties or characteristics given to material by treatment or manufacturing · CPC title

• B23P9/00

  Treating or finishing surfaces mechanically, with or without calibrating, primarily to resist wear or impact, e.g. smoothing or roughening turbine blades or bearings (treatment covered by a single other subclass, see the relevant subclass, e.g. B24C, C21D7/00, C22F1/00); Features of such surfaces not otherwise provided for, their treatment being unspecified · CPC title

• B23P6/045

  of turbine components, e.g. moving or stationary blades, rotors, etc. · CPC title

• B23P6/002 Primary

  Repairing turbine components, e.g. moving or stationary blades, rotors, (B23P6/045 takes precedence) · CPC title