Turbine blade repair

• US 4,611,744 A
• Filed: 06/20/1983
• Issued: 09/16/1986
• Est. Priority Date: 06/23/1982
• Status: Expired due to Fees

• Current Assignee: Refurbished Turbine Components Limited George Baylis Road Droiwich
• Original Assignee: Refurbished Turbine Components Ltd.
• Inventors: Fraser, Michael J., Legros, Raymond D.
• Primary Examiner(s): Ramsey, Kenneth J.
• Application Number:
  US06/505,775
• Time in Patent Office: 1,184 Days
• Field of Search: 228/119, 228/231, 228/232, 29/156.8 B
• US Class Current: 228/119
• CPC Class Codes: B23P 6/007 using only additive methods, e.g. build-up welding
• CPC Class Codes: B23P 6/045 of turbine components, e.g. moving or stationary blades, rotors, etc.
• CPC Class Codes: C21D 9/50 for welded joints
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling
• CPC Class Codes: Y10T 29/49746 by applying fluent material, e.g., coating, casting

Abstract

A method of repairing turbine blades including a repair step which involves the application of substantial thermal energy to the blade such as a welding or brazing operation includes a pre-heating step in which the blade is heated to a predetermined temperature in a controlled manner. The controlled heating may be continued both during the repair step involving the application of substantial thermal energy and after the repair step in order to minimize stress in the blade due to the application of considerable thermal energy to the blade.

Claims

1. A method of repairing a turbine blade, said method comprising the steps of:

(a) applying heating means to selected areas of a turbine blade to be repaired;

(b) heating said areas of the turbine blade to desired temperatures;

(c) carrying out a repair step on said blade, said repair step involving the application of substantial thermal energy to the blade;

(d) controlling said heating means during said repair step so as to heat said selected areas in a manner to reduce forces acting upon the blade due to the occurrence of thermal expansion in the blade resulting from application of said substantial thermal energy;

(e) said heating means being positioned so that the heat transferred to the turbine blade tends to cause distortion of said blade in a direction substantially opposite to the distortion which is likely to be caused by the repair step involving the application of said substantial thermal energy;

(f) controlling said heating means after said repair step so as to maintain said turbine blade at a predetermined temperature for a predetermined length of time.

2. A method of repairing a turbine blade as claimed in claim 1 wherein after said repair step involving application of substantial thermal energy, said blade is heated in a controlled manner to maintain said turbine blade at a temperature, or series of different temperatures, for a predetermined length of time so as to eliminate or substantially reduce stress present in said blade.

3. A method of repairing a turbine blade according to claim 1 wherein said heating means comprises electrically energized heating means.

4. A method of repairing a turbine blade according to claim 1 wherein the area to be repaired is surrounded during the repair step involving the application of substantial thermal energy by an inert atmosphere.

5. A method of repairing a crack in a turbine blade according to claim 1 wherein a substantial amount of material is removed from the turbine blade in the area of the crack and wherein said repair step involving the application of substantial thermal energy is commenced in a region surrounding the innermost end of said crack and finishes adjacent an edge region of said turbine blade.

6. A method of repairing a turbine blade according to claim 5 wherein the material of the fused metal is different from that of the parent material of the blade and is endowed when in its solidified state with more inherent resilience than the parent material of the blade.

7. A method of repairing a turbine blade according to claim 5 wherein the area to be repaired is surrounded during the repair step involving the application of substantial thermal energy by an inert atmosphere.

8. A method of repairing a turbine blade according to claim 1 wherein said repair step involving the application of substantial thermal energy comprises a welding or brazing operation and which operation is carried out from one side of said blade and wherein a backing member is provided on the other side of the blade, said backing member being provided with passages and a supply of inert gas whereby said inert gas is connected to said passages to enable the repair area to be surrounded by an inert atmosphere.

9. A method of repairing a turbine blade according to claim 1 wherein automatic control means are provided to control means for heating the blade in a controlled manner.

10. A method of repairing a turbine blade according to claim 1 wherein said blade is part of an array in which a plurality of blades are connected together by connecting means wherein said repair involves a repair step involving the application of substantial thermal energy to the turbine blade and wherein prior to the application of said substantial thermal energy at least a part of said turbine blade in the area of the repair is heated in a controlled manner and wherein one or more adjacent turbine blades are heated in a controlled manner.

11. A method of repairing a turbine blade according to claim 10 wherein said one or more adjacent turbine blades are heated to a temperature less than the temperature to which the blade to be repaired is heated.

12. A method of repairing a plurality of substantially similar or identical turbine blades in accordance with the method of claim 1, further including the steps of:

(a) repairing one of said blades;

(b) analyzing the structure of the first repaired blade;

(c) repeating the repair steps of claim 1 and the analyzing step (b) on the same or a second blade; and

(d) repairing the remaining blades while controlling the heating of said remaining blades to obtain the most satisfactory results obtained from said analysis of step (b).