Method of regenerating stator vane of gas turbine and gas turbine

• US 20070039177A1
• Filed: 08/01/2005
• Published: 02/22/2007
• Est. Priority Date: 08/03/2004
• Status: Abandoned Application

• Current Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Original Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Inventors: Saito, Daizo, Fuse, Toshiaki, Okamoto, Hiroaki, Ishibashi, Kazutoshi, Nakahashi, Masako, Yoshioka, Yomei
• Application Number:
  US11/193,639
• Publication Number:
  US 20070039177A1
• Time in Patent Office: Days
• US Class Current: 29/889.100
• CPC Class Codes: B23K 1/0018 Brazing of turbine parts
• CPC Class Codes: B23K 20/021 Isostatic pressure welding
• CPC Class Codes: B23K 2101/001 Turbines
• CPC Class Codes: B23P 6/007 using only additive methods, e.g. build-up welding
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling
• CPC Class Codes: Y10T 29/49732 by attaching repair preform, e.g., remaking, restoring, or patching
• CPC Class Codes: Y10T 29/49737 Metallurgically attaching preform

Abstract

A method of regenerating gas-turbine stator vane comprising the steps of: grinding the oxidized layer and the cracks 2 formed at surface portion so that a part of the cracks 2 remains; filling an equivalent material and a brazing material 4 into the ground portion, the equivalent material 3 having an equality with the base material 1 for the stator vane, and the brazing material 4 having a melting point lower than that of the equivalent material 3; heat treating the filled portion under pressurized inert gas atmosphere so as to melt the brazing material; performing brazing treatment by diffusing the molten brazing material into the cracked portions. According to the above method, the stator vane occurred with material deterioration and damages or the like due to operation of a gas turbine can be efficiently regenerated to provide a high quality without requiring to completely grinding and removing the cracks including a closed crack formed at surface of the stator vane.

Claims

1. A method of regenerating gas-turbine stator vane composed of base material and having cracks formed in the base material and oxidized layer formed at surface portion of the base material, the method comprising the steps of:

grinding the oxidized layer and the cracks so that a part of the cracks remains thereby to form a ground portion;

filling an equivalent material and a brazing material into said ground portion thereby to form a filled portion, said equivalent material having an equality with said base material for the stator vane, and said brazing material having a melting point lower than that of said equivalent material;

heat treating said filled portion under pressurized inert gas atmosphere so as to melt the brazing material;

performing brazing treatment by diffusing the molten brazing material into the cracked portions.

2. A method of regenerating gas-turbine stator vane according to claim 1, wherein when a total length of said cracks is longer than a chord length of the stator vane, the oxidized layer formed on entire surface of the stator vane is ground and the cracked portions are ground without completely grinding the cracked portion so that a part of the cracks remains, then an entire stator vane is covered with the equivalent material and the brazing material so as to completely repair the cracks.

3. A method of regenerating gas-turbine stator vane according to claim 1, wherein said brazing treatment is performed under the pressurized inert gas atmosphere by using a mixture of said brazing material and said equivalent material, said brazing treatment being performed as a repairing operation after the oxidized layer formed at the surface of the stator vane is removed, thereafter the repaired stator vane is subjected to a solution heat treatment and an aging heat treatment.

4. A method of regenerating gas-turbine stator vane according to claim 3, wherein said inert gas atmosphere is controlled to have a pressure of 95 to 200 MPa, while said solution heat treatment and the aging heat treatment are performed at a temperature lower than a temperature at which said base material is partially molten, or performed at a temperature lower than a temperature at which a cell structure formed of eutectic carbide is collapsed.

5. A method of regenerating gas-turbine stator vane according to claim 4, wherein said temperature in said solution heat treatment and the aging heat treatment is set to 1100-1300°

C.

6. A method of regenerating gas-turbine stator vane according to claim 1, wherein said equivalent material has a composition containing 20-35 wt % of Cr, 5-60 wt % of Ni, 0.5-2 wt % of Fe, 5-10 wt % of W, 0.1-0.5 wt % of C, 0.005-2 wt % of B, and balance of Co, while said brazing material has a composition containing 10-40 wt % of Cr, 8.5-70 wt % of Ni, 0.5-2 wt % of Fe, 9 wt % or less (including 0%) of W, 0.001-0.6 wt % of C, 0.01-3.5 wt % of B, 1.0-11 wt % of Si, 2 wt % or less (not including 0%) of Mn, and balance of Co.

7. A method of regenerating gas-turbine stator vane according to claim 1, wherein said equivalent material has a composition containing 5-35 wt % of Cr, 5-75 wt % of Ni, 2 wt % or less (including 0%) of Fe, 12 wt % or less (not including 0%) of W, 0.6 wt % or less (not including 0%) of C, 1 wt % or less (including 0%) of B, 2 wt % or less (including 0%) of Hf, 6 wt % or less (not including 0%) of Ti, 3 wt % or less (not including 0%) of Nb, 5 wt % or less (including 0%) of Re, 5 wt % or less (including 0%) of Mo, 8 wt % or less (not including 0%) of Ta, 65 wt % or less (not including 0%) of Al, 0.7 wt % or less (including 0%) of Zr, and balance (5-65%) of Co, while said brazing material has a composition containing 10-40 wt % of Cr, 8.5-70 wt % of Ni, 0.5-2 wt % of Fe, 9 wt % or less (including 0%) of W, 0.001-0.6 wt % of C, 0.01-3.5 wt % of B, 1.0-11 wt % of Si, 2 wt % or less (not including 0%) of Mn, and balance of Co.

8. A method of regenerating gas-turbine stator vane according to claim 1, wherein said equivalent material and said brazing material are filled into the ground portion so as to form a powder mixture layer having a three-layered structure comprising:

an outermost layer formed at the surface of the stator vane, a base-side layer formed at the surface of the base material of the stator vane, and an intermediate layer formed between the outermost layer and the base-side layer,

wherein an amount ratio of the brazing material contained in the outermost layer or the base-side layer is larger than that of the intermediate layer, while an amount ratio of the equivalent material contained in the intermediate layer is larger than that of the outermost layer or the base-side layer, or

the amount ratio of the brazing material is step-wisely or continuously increased in a range from the intermediate layer toward the outermost layer or the base-side layer.

9. A gas-turbine stator vane which is regenerated in accordance with the regenerating method according to claim 1.

10. A gas-turbine provided with the stator vane according to claim 9.

11. A gas-turbine stator vane which is regenerated in accordance with the regenerating method according to claim 2.

12. A gas-turbine stator vane which is regenerated in accordance with the regenerating method according to claim 3.

13. A gas-turbine stator vane which is regenerated in accordance with the regenerating method according to claim 4.

14. A gas-turbine stator vane which is regenerated in accordance with the regenerating method according to claim 5.

15. A gas-turbine stator vane which is regenerated in accordance with the regenerating method according to claim 6.

16. A gas-turbine stator vane which is regenerated in accordance with the regenerating method according to claim 7.