JPH07102996A - Repair of gas turbine moving blade - Google Patents
Repair of gas turbine moving bladeInfo
- Publication number
- JPH07102996A JPH07102996A JP26835893A JP26835893A JPH07102996A JP H07102996 A JPH07102996 A JP H07102996A JP 26835893 A JP26835893 A JP 26835893A JP 26835893 A JP26835893 A JP 26835893A JP H07102996 A JPH07102996 A JP H07102996A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- crack
- blade
- moving blade
- respect
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000463 material Substances 0.000 claims abstract description 27
- 239000000956 alloy Substances 0.000 claims abstract description 16
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 15
- 239000002344 surface layer Substances 0.000 claims abstract description 12
- 238000005219 brazing Methods 0.000 claims abstract description 11
- 239000010410 layer Substances 0.000 claims abstract description 10
- 238000007747 plating Methods 0.000 claims abstract description 10
- 239000000945 filler Substances 0.000 claims abstract description 8
- 238000009792 diffusion process Methods 0.000 claims abstract description 7
- 238000000034 method Methods 0.000 claims description 9
- 238000001513 hot isostatic pressing Methods 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 2
- 238000003466 welding Methods 0.000 abstract description 12
- 230000002706 hydrostatic effect Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 19
- 239000010953 base metal Substances 0.000 description 5
- 238000007750 plasma spraying Methods 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000008929 regeneration Effects 0.000 description 1
- 238000011069 regeneration method Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
- B23P6/045—Repairing fractures or cracked metal parts or products, e.g. castings of turbine components, e.g. moving or stationary blades, rotors, etc.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、Ｎｉ基耐熱合金で形成
されているガスタービン動翼の運転後の補修法に関す
る。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for repairing a gas turbine rotor blade made of a Ni-base heat-resistant alloy after its operation.
【０００２】[0002]
【従来の技術】長時間運転に供した後のガスタービン動
翼は高温ガス流れにさらされるため材料強度が低下し、
エロージョン、コロージョン等によってガス入口側は減
肉し、かつ表層には開口したクラックが存在しているこ
とが多い。2. Description of the Related Art A gas turbine blade after being operated for a long time is exposed to a high temperature gas flow, so that the material strength is lowered,
In many cases, the gas inlet side is thinned due to erosion, corrosion, etc., and open cracks are present in the surface layer.
【０００３】図２はこのような長時間運転に供した後の
ガスタービン動翼１を示し、翼全面に酸化膜２が堆積す
ると共に、一部には減肉３、クラック４が発生してい
る。FIG. 2 shows a gas turbine rotor blade 1 after being subjected to such a long-term operation. An oxide film 2 is deposited on the entire surface of the blade, and a thinned portion 3 and a crack 4 are partially generated. There is.
【０００４】このため、これらの減肉部、クラックの補
修が必要となるが、ガスタービン動翼がＮｉ基の耐熱合
金で形成されている場合、その補修は通常低圧プラズマ
溶射で行われている。Therefore, it is necessary to repair these thinned portions and cracks. When the gas turbine blade is made of a Ni-base heat-resistant alloy, the repair is usually performed by low pressure plasma spraying. .
【０００５】[0005]
【発明が解決しようとする課題】ところで、この低圧プ
ラズマ溶射は、摩耗個所やクラックの補修・再生に適し
た方法であるが、Ｎｉ基の耐熱合金材料に適合した溶射
材料の選定が難しく、選定に当っては融点、母材との熱
膨張係数とのマッチングなども考慮しなければならな
い。そのため、低圧プラズマ溶射では、どうしてもガス
タービン動翼の補修部を母材強度まで回復させることが
できない問題があった。By the way, this low-pressure plasma spraying is a method suitable for repairing and regenerating wear spots and cracks, but it is difficult to select a spraying material suitable for a Ni-based heat-resistant alloy material. In this case, it is necessary to consider the melting point and matching with the coefficient of thermal expansion of the base material. Therefore, in the low pressure plasma spraying, there was a problem that the repaired portion of the gas turbine blade could not be restored to the base metal strength.
【０００６】本発明は、このような従来技術の課題を解
決するためになされたもので、減肉部及び／又はクラッ
クの補修部を母材強度と殆んど同等の強度とすることが
できるガスタービン動翼の補修法を提供することを目的
とする。The present invention has been made in order to solve the problems of the prior art as described above, and it is possible to make the thinned portion and / or the repaired portion of the crack have almost the same strength as the base metal strength. An object is to provide a method for repairing a gas turbine blade.
【０００７】[0007]
【課題を解決するための手段】上記の課題を解決するた
めに、本発明は、運転に供した後のＮｉ基耐熱合金製の
ガスタービン動翼の減肉部に対し該動翼と同一の材料
（Ｎｉ基耐熱合金）の溶加材をティグ（ＴＩＧ）溶接
し、次に前記動翼の表層部に生じたクラックに対しＮｉ
メッキ及びＮｉロー付けを行う拡散処理を施し、その後
深層部のクラックに対して熱間静水圧プレス処理を施す
ようにしたものである。SUMMARY OF THE INVENTION In order to solve the above problems, the present invention provides a gas turbine rotor blade made of a Ni-base heat-resistant alloy after being put into operation with the same thin wall portion as the rotor blade. The filler material of the material (Ni-based heat-resistant alloy) is TIG welded, and then Ni is applied to cracks generated in the surface layer portion of the moving blade.
Diffusion treatment is performed by plating and Ni brazing, and then hot isostatic pressing is performed on cracks in the deep layer.
【０００８】また、本発明によれば、運転に供した後の
Ｎｉ基耐熱合金製のガスタービン動翼の表層部に生じた
クラックに対し該動翼と同一の材料（Ｎｉ基耐熱合金）
の溶加材をティグ溶接し、次にＮｉメッキ及びＮｉロー
付けを行う拡散処理を施し、その後深層部のクラックに
対して熱間静水圧プレス処理を施すようにしたものであ
る。According to the present invention, the same material (Ni-based heat-resistant alloy) as that of the cracks generated in the surface layer of the gas turbine blade made of the Ni-based heat-resistant alloy after being used for operation is used.
TIG welding the filler material of No. 2 and then performing a diffusion process of Ni plating and Ni brazing, and then performing hot isostatic pressing on cracks in the deep layer.
【０００９】[0009]
【作用】上記の手段によれば、運転に供した後のＮｉ基
耐熱合金製のガスタービン動翼において、減肉部及び／
又はクラックの補修部を該動翼母材と同じ材料でティグ
溶接することにより、母材強度と殆んど同等の強度が得
られる。また、ティグ溶接により発生する熱影響部の表
層部及び母材深層部のクラックも、表層部のクラックは
Ｎｉメッキ及びＮｉロー付けにより補修できると共に、
母材深層部のクラックは熱間静水圧プレス処理によって
補修できる。According to the above means, in the gas turbine rotor blade made of the Ni-base heat-resistant alloy after being put into operation,
Alternatively, by performing TIG welding on the crack repair portion with the same material as the moving blade base material, strength almost equal to the base material strength can be obtained. Further, the cracks in the surface layer of the heat affected zone and the deep layer of the base metal generated by the TIG welding can be repaired by Ni plating and Ni brazing, and
Cracks in the deep part of the base material can be repaired by hot isostatic pressing.
【００１０】[0010]
【実施例】以下、図面を参照して本発明の一実施例につ
いて詳細に説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described in detail below with reference to the drawings.
【００１１】図２に示したように、長時間運転に供した
後のＮｉ基耐熱合金製のガスタービン動翼１は、翼全面
に酸化膜２が堆積するとともに、一部には減肉３、クラ
ック４が発生している。As shown in FIG. 2, in a gas turbine rotor blade 1 made of a Ni-base heat-resistant alloy after being used for a long period of time, an oxide film 2 is deposited on the entire surface of the blade, and a portion 3 is thinned. , Crack 4 has occurred.
【００１２】そこで、まず、動翼１の酸化膜２をグリッ
トブラスト等で除去する。それから、図１に示すよう
に、減肉３の部分に対して動翼１と同じ材料（Ｎｉ基耐
熱合金）の溶加材を不活性ガス（アルゴン、ヘリウムな
ど）でガスシールドして溶接するティグ溶接５を行う。Therefore, first, the oxide film 2 on the rotor blade 1 is removed by grit blasting or the like. Then, as shown in FIG. 1, a filler material made of the same material (Ni-based heat-resistant alloy) as the rotor blade 1 is gas shielded with an inert gas (argon, helium, etc.) and welded to the thinned portion 3. Perform TIG welding 5.
【００１３】そして、表層部のクラック４に対しては、
Ｎｉメッキ及びＮｉロー付け６をすることにより拡散処
理して塞ぐ。この場合、長時間運転により動翼１の表層
部に生じたクラック４に加え、上記のティグ溶接５によ
り熱影響部の表層部に他のクラックが生ずることがある
ので、この他のクラック（図示せず）に対してもＮｉメ
ッキ及びＮｉロー付けをすることにより拡散処理して塞
ぐ。Then, for the crack 4 on the surface layer,
Ni plating and Ni brazing 6 are performed to diffuse and close the plug. In this case, in addition to the crack 4 generated in the surface layer portion of the rotor blade 1 due to long-time operation, other cracks may occur in the surface layer portion of the heat-affected zone due to the TIG welding 5 described above. (Not shown) is also plated with Ni and brazed with Ni to diffuse and close.
【００１４】また、上記のティグ溶接５により熱影響部
の母材深層部にもクラックが生ずることがあるので、こ
の母材深層部に発生したクラック（図示せず）に対して
は、熱間静水圧プレス処理を施す。この熱間静水圧プレ
ス処理では、外表面より均一にかつ高温下で圧力を加え
るため、内部欠陥、内部組織については改質されるが、
表面開口部には圧力が加わらない。Further, since the TIG welding 5 may cause a crack in the deep part of the base material in the heat-affected zone, a crack (not shown) generated in the deep part of the base material can be hot worked. Apply hydrostatic pressing. In this hot isostatic pressing process, pressure is applied more uniformly and at a higher temperature than the outer surface, so internal defects and internal structures are modified,
No pressure is applied to the surface opening.
【００１５】更に、変形例として、長時間運転に供した
後のＮｉ基耐熱合金製のガスタービン動翼１の表層部に
生じたクラック４に対し動翼１と同一の材料（Ｎｉ基耐
熱合金）の溶加材をティグ溶接し、次にＮｉメッキ及び
Ｎｉロー付けを行う拡散処理を施し、その後深層部のク
ラックに対して熱間静水圧プレス処理を施すようにする
こともできる。Further, as a modified example, the same material as the blade 1 (Ni-based heat-resistant alloy) is used for cracks 4 generated in the surface layer portion of the gas turbine blade 1 made of a Ni-based heat-resistant alloy after being used for a long time. It is also possible to perform TIG welding of the filler metal of 1), then perform a diffusion process of performing Ni plating and Ni brazing, and then perform hot isostatic pressing on cracks in the deep layer.
【００１６】[0016]
【発明の効果】以上述べたように、本発明によれば、運
転に供した後のＮｉ基耐熱合金製のガスタービン動翼に
おいて、減肉部及び／又はクラックの補修部を該動翼母
材と同じ材料でティグ溶接することにより、母材強度と
殆んど同等の強度が得られる。また、ティグ溶接により
発生する熱影響部の表層部及び母材深層部のクラック
も、表層部のクラックはＮｉメッキ及びＮｉロー付けに
より補修できると共に、母材深層部のクラックは熱間静
水圧プレス処理によって補修でき、それぞれの補修法に
より適切に処理できる。従って、ガスタービン動翼の補
修・再生に寄与する効果は極めて大きいものがある。As described above, according to the present invention, in a gas turbine rotor blade made of a Ni-base heat-resistant alloy after being put into operation, the thin wall portion and / or the crack repair portion is provided in the rotor mother board. By TIG welding with the same material as the base material, strength almost equal to the base material strength can be obtained. Also, cracks in the surface layer of the heat-affected zone and deep layer of the base metal generated by TIG welding can be repaired by Ni plating and Ni brazing, and cracks in the deep layer of the base metal can be hot isostatic pressed. It can be repaired by treatment and can be properly treated by each repair method. Therefore, the effect of contributing to the repair / regeneration of the gas turbine blade is extremely large.
【図１】本発明に係るガスタービン動翼の補修法の一実
施例を説明するための動翼斜視図である。FIG. 1 is a perspective view of a moving blade for explaining an embodiment of a method for repairing a gas turbine moving blade according to the present invention.
【図２】長時間の運転に供した後のガスタービン動翼を
示す斜視図である。FIG. 2 is a perspective view showing a gas turbine rotor blade after being subjected to long-term operation.
１ ガスタービン動翼 ２ 酸化膜 ３ 減肉 ４ クラック ５ ティグ溶接 ６ Ｎｉメッキ及びＮｉロー付け 1 Gas turbine rotor blade 2 Oxide film 3 Thinning 4 Crack 5 Tig welding 6 Ni plating and Ni brazing
Claims (2)
タービン動翼の減肉部に対し該動翼と同一の材料の溶加
材をティグ溶接し、次に前記動翼の表層部に生じたクラ
ックに対しＮｉメッキ及びＮｉロー付けを行う拡散処理
を施し、その後深層部のクラックに対して熱間静水圧プ
レス処理を施すことを特徴とする、ガスタービン動翼の
補修法。1. A filler material made of the same material as the blade is TIG-welded to a thinned portion of a gas turbine blade made of a Ni-base heat-resistant alloy after being subjected to operation, and then a surface layer of the blade. A repair method for a gas turbine rotor blade, which comprises subjecting a crack generated in a portion to a diffusion treatment of Ni plating and Ni brazing, and then performing a hot isostatic pressing treatment to a crack in a deep layer portion.
タービン動翼の表層部に生じたクラックに対し該動翼と
同一の材料の溶加材をティグ溶接し、次にＮｉメッキ及
びＮｉロー付けを行う拡散処理を施し、その後深層部の
クラックに対して熱間静水圧プレス処理を施すことを特
徴とする、ガスタービン動翼の補修法。2. A filler metal made of the same material as that of the blade is TIG-welded to a crack generated in the surface layer of the gas turbine blade made of a Ni-base heat-resistant alloy after being subjected to operation, and then Ni-plated. And a method of repairing a gas turbine rotor blade, which comprises performing a diffusion process of performing Ni brazing, and then performing a hot isostatic pressing process on a crack in a deep layer portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26835893A JP3181157B2 (en) | 1993-09-30 | 1993-09-30 | Repair method of gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP26835893A JP3181157B2 (en) | 1993-09-30 | 1993-09-30 | Repair method of gas turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH07102996A true JPH07102996A (en) | 1995-04-18 |
| JP3181157B2 JP3181157B2 (en) | 2001-07-03 |
Family
ID=17457416
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP26835893A Expired - Fee Related JP3181157B2 (en) | 1993-09-30 | 1993-09-30 | Repair method of gas turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3181157B2 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001123237A (en) * | 1999-10-04 | 2001-05-08 | General Electric Co <Ge> | Superalloy welded composition and repaired turbine engine parts |
| JP2007040303A (en) * | 2005-08-01 | 2007-02-15 | General Electric Co <Ge> | Method of restoring part of turbine structural element |
| CN103551794A (en) * | 2013-10-21 | 2014-02-05 | 中国科学院金属研究所 | High temperature alloy hot end part large gap defect transient state liquid phase infiltration repairing method |
| EP2900416A4 (en) * | 2012-09-28 | 2016-05-25 | United Technologies Corp | Repair of casting defects |
| CN115722866A (en) * | 2022-12-07 | 2023-03-03 | 中国航发动力股份有限公司 | A single crystal blade welding cover plate repair method |
-
1993
- 1993-09-30 JP JP26835893A patent/JP3181157B2/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001123237A (en) * | 1999-10-04 | 2001-05-08 | General Electric Co <Ge> | Superalloy welded composition and repaired turbine engine parts |
| JP2007040303A (en) * | 2005-08-01 | 2007-02-15 | General Electric Co <Ge> | Method of restoring part of turbine structural element |
| EP2900416A4 (en) * | 2012-09-28 | 2016-05-25 | United Technologies Corp | Repair of casting defects |
| CN103551794A (en) * | 2013-10-21 | 2014-02-05 | 中国科学院金属研究所 | High temperature alloy hot end part large gap defect transient state liquid phase infiltration repairing method |
| CN103551794B (en) * | 2013-10-21 | 2016-01-13 | 中国科学院金属研究所 | High temperature alloy hot-end component wide arc gap defect Transient liquid phase infiltration restorative procedure |
| CN115722866A (en) * | 2022-12-07 | 2023-03-03 | 中国航发动力股份有限公司 | A single crystal blade welding cover plate repair method |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3181157B2 (en) | 2001-07-03 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
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Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20010313 |
|
| LAPS | Cancellation because of no payment of annual fees |