JP5941375B2 - Laser overlay welding apparatus and manufacturing method of overlay weld parts - Google Patents
Laser overlay welding apparatus and manufacturing method of overlay weld parts Download PDFInfo
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- JP5941375B2 JP5941375B2 JP2012188203A JP2012188203A JP5941375B2 JP 5941375 B2 JP5941375 B2 JP 5941375B2 JP 2012188203 A JP2012188203 A JP 2012188203A JP 2012188203 A JP2012188203 A JP 2012188203A JP 5941375 B2 JP5941375 B2 JP 5941375B2
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- 238000003466 welding Methods 0.000 title claims description 35
- 238000004519 manufacturing process Methods 0.000 title claims description 10
- 239000000843 powder Substances 0.000 claims description 87
- 239000000945 filler Substances 0.000 claims description 35
- 239000000463 material Substances 0.000 claims description 33
- 238000007711 solidification Methods 0.000 claims description 31
- 230000008023 solidification Effects 0.000 claims description 31
- 239000013078 crystal Substances 0.000 claims description 24
- 239000004065 semiconductor Substances 0.000 claims description 13
- 230000001678 irradiating effect Effects 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 7
- 238000004587 chromatography analysis Methods 0.000 claims description 6
- 238000010276 construction Methods 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 125000004122 cyclic group Chemical group 0.000 claims description 4
- 239000000289 melt material Substances 0.000 claims 1
- 239000007789 gas Substances 0.000 description 41
- 238000004372 laser cladding Methods 0.000 description 11
- 238000005336 cracking Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 230000008018 melting Effects 0.000 description 3
- 239000013307 optical fiber Substances 0.000 description 3
- 239000012159 carrier gas Substances 0.000 description 2
- 238000002425 crystallisation Methods 0.000 description 2
- 230000008025 crystallization Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
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Description
本発明はレーザ肉盛溶接装置、及び肉盛溶接部品の製造方法に関する。 The present invention relates to a laser overlay welding apparatus and a method for manufacturing an overlay welding component.
近年、ニアネットシェイプの直接造形、補修や耐摩耗性などの機能付与を目的とした表面処理技術等にパウダを溶加材としたレーザ肉盛が用いられている。ガスタービン翼では高温での強度に優れた材料が採用されているため、割れ感受性が高く、溶接補修が難しい。また最近では凝固組織制御された単結晶翼も使用されており、補修部の凝固組織制御による単結晶化も要求され始めている。凝固組織制御には熱流、温度勾配や成長速度の制御が必要となるが、溶接の場合にはこれらの制御は困難である。その解決策として、特許文献１には、補修部における凝固速度（G）と溶融境界における温度勾配（G）の比（G/R）が、方向凝固結晶を生じさせる値3×104℃・Sec/cm2以上になるように、入熱量および加熱パターンを制御する方法が提案されている。 In recent years, laser cladding using powder as a filler material has been used for surface treatment technology for the purpose of imparting functions such as direct shaping, repair and wear resistance of near net shape. Since gas turbine blades use materials with excellent strength at high temperatures, they are highly susceptible to cracking and difficult to repair. Recently, single crystal wings with controlled solidification structure have been used, and single crystallization by controlling the solidification structure of repaired parts has begun to be required. Control of the solidification structure requires control of heat flow, temperature gradient, and growth rate, but these controls are difficult in the case of welding. As a solution, Patent Document 1 discloses that the ratio (G / R) of the solidification rate (G) at the repaired portion and the temperature gradient (G) at the melting boundary is a value that produces a directionally solidified crystal of 3 × 10 4 ° C A method of controlling the amount of heat input and the heating pattern so as to be Sec / cm 2 or more has been proposed.
特許文献１に記載の方法では、積層部の結晶方位を母材と同一方向になるよう積層させる場合には、最大温度勾配の方向を母材結晶の優先成長方向に沿った方向に制御することが難しく、結晶方位の異なる結晶が発生する可能性が高くなる。これは、積層の高さが高くなるとその傾向が顕著であり、複数回の積層を行う場合には、異結晶の発生は避けられない。このように単結晶翼の溶接補修部に異結晶が生成すると、溶接割れしやすいという課題がある。 In the method described in Patent Document 1, in the case of stacking so that the crystal orientation of the stacked portion is in the same direction as the base material, the direction of the maximum temperature gradient is controlled to the direction along the preferential growth direction of the base crystal. It is difficult to generate crystals with different crystal orientations. This tendency is conspicuous when the height of the stack increases, and the occurrence of different crystals is inevitable when stacking is performed a plurality of times. Thus, when a different crystal | crystallization produces | generates in the welding repair part of a single crystal blade, there exists a subject that it is easy to weld crack.
本発明の目的は、溶接部の溶接割れを抑制することにある。 An object of the present invention is to suppress weld cracking of a welded portion.
上記目的を達成するため、本発明は、所定の施工対象物の表面に肉盛溶接を行うレーザ肉盛溶接装置であって、前記所定の施工対象物は方向凝固制御された結晶組織を有するガスタービン翼であり、前記表面は前記ガスタービン翼の上端部の環状表面であり、前記環状表面にレーザを照射して環状の溶融池を形成するヘッドと、前記環状の溶融池に溶加材を供給する溶加材供給部とを備え、前記ヘッドは、溶接施工している間は前記環状の溶融池の全てが溶融状態を保持するように、前記環状表面に沿って前記レーザを走査させるミラー回転機構又は前記環状表面の全てに対して前記レーザを常に照射する半導体レーザ発生部を備え、前記溶加材供給部は、供給した前記溶加材が溶融凝固して肉盛部を形成する際に該肉盛部の成長が前記ガスタービン翼の結晶組織の優先成長方向と一致した指向性凝固となるように、前記環状の溶融池に沿って均一に前記溶加材を供給し続ける構造又は機構を備えることを特徴とする。 In order to achieve the above object, the present invention is a laser overlay welding apparatus for performing overlay welding on the surface of a predetermined construction object, wherein the predetermined construction object is a gas having a crystal structure whose direction solidification is controlled. a turbine blade, said surface is annular surface of the upper portion of the gas turbine blade, a head for forming a molten pool of cyclic by irradiating Les chromatography the said annular surface, filler to the molten pool of the annular e Bei a filler metal supply unit for supplying the timber, the head, the while welding so that all of the molten pool of said annular holding a molten state, the laser along said annular surface A mirror rotating mechanism to be scanned or a semiconductor laser generating unit that constantly irradiates the laser to all of the annular surface, and the filler material supplying unit is configured to melt and solidify the supplied filler material. When forming, the build-up portion grows as the gas. So that the matched directional solidification and preferential growth direction of the crystal structure of the turbine blades, characterized in that it comprises a structure or mechanism continues to supply uniformly the filler material along a molten pool of said annular.
また、本発明は、所定の施工対象物の表面にレーザ肉盛溶接を行った肉盛溶接部品の製造方法であって、前記所定の施工対象物は方向凝固制御された結晶組織を有するガスタービン翼であり、前記表面は前記ガスタービン翼の上端部の環状表面であり、前記環状表面にレーザを照射して環状の溶融池を形成する工程と、前記環状の溶融池に溶加材を供給する工程とを有し、前記環状の溶融池を形成する工程は、溶接施工している間は前記環状の溶融池の全てが溶融状態を保持するように、前記環状の溶融池が全て凝固する前に前記レーザを再照射する又は前記環状の溶融池の全てに対して前記レーザを常に照射する工程であり、前記溶加材を供給する工程は、供給した前記溶加材が溶融凝固して肉盛部を形成する際に該肉盛部の成長が前記ガスタービン翼の結晶組織の優先成長方向と一致した指向性凝固となるように、前記環状の溶融池に沿って均一に前記溶加材を供給し続ける工程であることを特徴とする。 Further, the present invention provides a method for producing a predetermined execution object overlay welding parts was Les chromatography The overlay welding on a surface of said predetermined execution object has a crystalline structure which is a directional solidification control a gas turbine blade, said surface is annular surface of the upper portion of the gas turbine blade, and forming a molten pool of cyclic by irradiating Les chromatography the said annular surface, soluble in molten pool of said annular the pressure member and a supplying step of forming a molten pool of said annular, the while welding so that all of the molten pool of said annular holding a molten state, the annular melt pool Is the step of re- irradiating the laser before all solidifies or always irradiating the laser to all of the annular molten pool, and the step of supplying the filler material includes the step of supplying the filler material When the overlay is formed by melting and solidifying, the growth of the overlay is As will be matched directional solidification and preferential growth direction of the crystal structure of the turbine blade, characterized in that it is a step of continuously supplying a uniform said filler material along a molten pool of said annular.
本発明によれば、溶接部の溶接割れを抑制することができる。 According to the present invention, it is possible to suppress weld cracks in the welded portion.
以下、実施例を図面を用いて説明する。 Hereinafter, examples will be described with reference to the drawings.
図１に実施例１のレーザ肉盛装置の外観模式図を示す。本実施例ではガスタービン翼の補修を施行対象物としているが、レーザ照射部に溶加材を供給しながら、レーザが表面を走査して肉盛溶接するものであればよい。１はレーザ発振器、２は光ファイバ、３はスキャナーヘッド、４はレーザ、５はガスタービン翼、６は加工テーブル、７はパウダフィーダ、８はパウダ（溶加材）、９はパウダ供給部、１０は溶融池を示している。レーザ発振器１で生成されたレーザは光ファイバ２を通じて、スキャナーヘッド３に送られる。スキャナーヘッドで集光、位置決めされたレーザ４はガスタービン翼５に照射される。レーザ４の照射によりガスタービン翼５の表面に溶融池１０が形成される。パウダフィーダ７からキャリアガスとともに送給されたパウダはパウダ供給部９を通じて、溶融池１０に送られる。スキャナーヘッド３を用いてレーザ４を溶接線上に高速走査させて、レーザ照射によって溶融した部分が凝固する前に、再度レーザ照射することで、溶接部が常に溶融している状態を保持した。レーザはスキャナーヘッド３の中に設けられたミラー（図示なし）を回転させることで高速操作させる。 The external appearance schematic diagram of the laser cladding apparatus of Example 1 is shown in FIG. In the present embodiment, repair of the gas turbine blade is an object to be implemented, but any laser beam may be used as long as the laser scans the surface and performs overlay welding while supplying the filler material to the laser irradiation portion. 1 is a laser oscillator, 2 is an optical fiber, 3 is a scanner head, 4 is a laser, 5 is a gas turbine blade, 6 is a processing table, 7 is a powder feeder, 8 is a powder (melting material), 9 is a powder supply unit, Reference numeral 10 denotes a molten pool. The laser generated by the laser oscillator 1 is sent to the scanner head 3 through the optical fiber 2. The laser 4 condensed and positioned by the scanner head is irradiated to the gas turbine blade 5. A molten pool 10 is formed on the surface of the gas turbine blade 5 by the irradiation of the laser 4. The powder fed from the powder feeder 7 together with the carrier gas is sent to the molten pool 10 through the powder supply unit 9. The laser 4 was scanned at high speed on the welding line using the scanner head 3, and the welded portion was always melted by irradiating the laser again before the melted portion solidified by the laser irradiation. The laser is operated at a high speed by rotating a mirror (not shown) provided in the scanner head 3.
図２はレーザ肉盛装置の拡大図である。図３はパウダ供給部を上から見た模式図である。１１はパウダ供給部の保持部、１２はパウダ供給管、１３はパウダ導入口である。溶接対象がガスタービン翼であるため、溶接線はガスタービン翼の上端の形状となる。そのため、本実施例ではガスタービン翼の上端部と同じ形状のパウダ供給部９を作製した。パウダ供給部９はパウダ供給部の保持部１１によって、スキャナーヘッド３に固定されている。パウダ供給部９はパウダの出口形状がガスタービン翼の上端部と同じ形状になっており、パウダを溶接部に振りかけるように供給することが可能である。また本実施例ではパウダ供給部９には１４個のパウダ導入口１３が設けられている。パウダ供給部９に対して複数箇所からパウダを供給することで、パウダ供給部内でパウダが偏りにくくなり、ガスタービン翼の上端部に均一にパウダを供給することができる。またレーザ４はパウダ供給部９の内側の空間を通過するように照射した。 FIG. 2 is an enlarged view of the laser cladding apparatus. FIG. 3 is a schematic view of the powder supply unit viewed from above. 11 is a holding part of the powder supply unit, 12 is a powder supply pipe, and 13 is a powder inlet. Since the object to be welded is a gas turbine blade, the weld line has the shape of the upper end of the gas turbine blade. Therefore, in this example, a powder supply unit 9 having the same shape as the upper end of the gas turbine blade was produced. The powder supply unit 9 is fixed to the scanner head 3 by a holding unit 11 of the powder supply unit. The powder supply unit 9 has a powder outlet shape that is the same as that of the upper end of the gas turbine blade, and can supply the powder so as to sprinkle on the welded part. In this embodiment, the powder supply unit 9 is provided with 14 powder introduction ports 13. By supplying the powder to the powder supply unit 9 from a plurality of locations, the powder is less likely to be biased in the powder supply unit, and the powder can be supplied uniformly to the upper end of the gas turbine blade. The laser 4 was irradiated so as to pass through the space inside the powder supply unit 9.
図４はレーザ肉盛部の断面を横から見た模式図である。１４Ａはレーザ４の進行方向（紙面手前方向）、１４Ｂはレーザ４の進行方向（紙面奥行方向）を示している。レーザ４をスキャナーヘッド３によって溶接線上を何度も高速に走査し続け、溶接線の凝固が完了する前にレーザ４を再照射する。これにより一連の溶接施工中では、溶接線の全線、即ちレーザが照射されていない時の溶接線においても溶融池１０が常に形成されている。そして溶融池１０の形状に合わせたパウダ供給部９から溶融池１０にパウダ８を供給し続けることにより、徐々に肉盛部を高く形成することができる。 FIG. 4 is a schematic view of the cross section of the laser cladding portion as viewed from the side. 14A indicates the traveling direction of the laser 4 (front direction on the paper surface), and 14B indicates the traveling direction of the laser 4 (depth direction on the paper surface). The laser 4 is continuously scanned over the weld line by the scanner head 3 many times, and the laser 4 is irradiated again before the solidification of the weld line is completed. As a result, during a series of welding operations, the weld pool 10 is always formed even on the entire welding line, that is, the welding line when the laser is not irradiated. And by continuing to supply the powder 8 to the molten pool 10 from the powder supply part 9 matched with the shape of the molten pool 10, the build-up part can be formed gradually high.
供給されるパウダが肉盛部に接触する際は、必ず肉盛部の表面が溶融した溶融池１０となっている。肉盛部の内部は肉盛部の形成に伴って凝固していくが、表面は溶融した状態を保っている。つまりガスタービン翼の上端部において、擬似的な鋳造によりパウダ供給部９に向かって肉盛部を成長させることができる。このときの熱流の方向は垂直（パウダ供給部９の方向）になり、母材であるガスタービン翼の結晶の優先成長方向と一致し、指向性凝固しやすい凝固条件となる。従って、ガスタービン翼と肉盛部との溶接部の割れを抑制することができる。またパウダ供給量を調整することで、肉盛部の成長速度を制御することも可能であり、さらに指向性凝固しやすい凝固条件を得ることが可能となる。 When the powder to be supplied comes into contact with the build-up portion, the surface of the build-up portion is always the molten pool 10 that is melted. The inside of the built-up part is solidified with the formation of the built-up part, but the surface is kept in a molten state. That is, at the upper end portion of the gas turbine blade, the overlay portion can be grown toward the powder supply portion 9 by pseudo casting. The direction of the heat flow at this time is vertical (in the direction of the powder supply unit 9), coincides with the preferential growth direction of the crystal of the gas turbine blade that is the base material, and becomes a solidification condition that facilitates directional solidification. Therefore, it is possible to suppress cracks in the welded portion between the gas turbine blade and the built-up portion. Further, by adjusting the powder supply amount, it is possible to control the growth rate of the built-up portion, and it is possible to obtain solidification conditions that facilitate directional solidification.
さらにガスタービン翼の下部を冷却することによって、より大きな温度勾配を得ることができ、指向性凝固しやすい凝固条件を得ることが可能となる。また溶接線が常に溶融しているため、本実施例のように溶接線が環状の場合は終始端が存在せず、終始端で発生しやすい割れや異結晶の発生が抑制可能である。 Furthermore, by cooling the lower part of the gas turbine blade, a larger temperature gradient can be obtained, and solidification conditions that facilitate directional solidification can be obtained. In addition, since the weld line is always melted, when the weld line is annular as in this embodiment, there is no starting end, and it is possible to suppress the generation of cracks and different crystals that are likely to occur at the starting end.
本実施例ではシールドガスを用いていないが、パウダ供給部９にシールドガス供給機構を設けたり、別のガスノズルを用いたり、雰囲気置換したりすることで、より安定したシールドが得られる。 Although no shield gas is used in this embodiment, a more stable shield can be obtained by providing a shield gas supply mechanism in the powder supply unit 9, using another gas nozzle, or replacing the atmosphere.
また本実施例ではパウダ供給部９に１４個のパウダ導入口１３を設けたが、パウダ導入口１３の数はこれに限定されない。
また本実施例では溶加材にパウダを用いたが、溶加材の形状はこれに限定されない。
また本実施例ではレーザ４はパウダ供給部９の内側の空間を通過させて照射したが、スキャナーヘッドを複数用意して、パウダ供給部９の外側から照射することも可能である。
In this embodiment, 14 powder inlets 13 are provided in the powder supply unit 9, but the number of powder inlets 13 is not limited to this.
In this embodiment, powder is used as the filler material, but the shape of the filler material is not limited to this.
In this embodiment, the laser 4 is irradiated through the space inside the powder supply unit 9. However, it is also possible to prepare a plurality of scanner heads and irradiate from the outside of the powder supply unit 9.
本実施例では、パウダ供給部が溶接部形状ではなく、管状部品で構成される場合を説明する。図５は実施例２のレーザ肉盛装置の外観模式図を示し、図６はレーザ肉盛装置の拡大図である。本実施例では実施例１と異なる点を中心に述べる。 In the present embodiment, a case where the powder supply unit is formed of a tubular part instead of a welded part shape will be described. FIG. 5 is a schematic external view of the laser cladding apparatus of Example 2, and FIG. 6 is an enlarged view of the laser cladding apparatus. In the present embodiment, differences from the first embodiment will be mainly described.
１５はパウダ供給部の駆動部、１６はパウダ供給部のレールである。溶接対象をガスタービン翼とすると、溶接線はガスタービン翼の上端の形状となる。本実施例では、パウダ供給部９自身を動かしながらパウダフィーダ７から送給されたパウダを溶融池１０に吹き付けた。パウダ供給部９が溶接線上を走査できるように、パウダ供給部９にはパウダ供給部の駆動部１５を設け、パウダ供給のレール１６上を駆動させることで、溶接線上にパウダを供給した。またパウダ供給部９はレーザ４とは独立しているため、パウダ供給部９の操作速度やパウダ供給量、パウダ供給位置を自由に調整することができる。 Reference numeral 15 denotes a drive unit of the powder supply unit, and 16 denotes a rail of the powder supply unit. If the object to be welded is a gas turbine blade, the weld line has the shape of the upper end of the gas turbine blade. In this embodiment, the powder supplied from the powder feeder 7 was sprayed on the molten pool 10 while moving the powder supply unit 9 itself. The powder supply unit 9 is provided with a drive unit 15 of the powder supply unit so that the powder supply unit 9 can scan the weld line, and the powder is supplied onto the weld line by driving the powder supply rail 16. Further, since the powder supply unit 9 is independent of the laser 4, the operation speed, the powder supply amount, and the powder supply position of the powder supply unit 9 can be freely adjusted.
本実施例でも、パウダ８が供給された分だけ肉盛部を形成することができ、肉盛部の表面を常に溶融させておくことができる。従って、熱流の方向とガスタービン翼の結晶の優先成長方向とが一致し、指向性凝固しやすい凝固条件となるので、ガスタービン翼と肉盛部との溶接部の割れを抑制することができる。またパウダ供給量を調整することで、成長速度を制御することが可能であり、指向性凝固しやすい凝固条件を得ることが可能となる。 Also in this embodiment, the build-up portion can be formed as much as the powder 8 is supplied, and the surface of the build-up portion can always be melted. Accordingly, the direction of heat flow matches the preferential growth direction of the crystal of the gas turbine blade, and the solidification conditions are likely to cause directional solidification, so that cracking of the welded portion between the gas turbine blade and the built-up portion can be suppressed. . Further, by adjusting the powder supply amount, it is possible to control the growth rate and to obtain a solidification condition that facilitates directional solidification.
さらにガスタービン翼の下部を冷却することによって、より大きな温度勾配を得ることができ、指向性凝固しやすい凝固条件を得ることが可能となる。また溶接線が常に溶融しているため、本実施例のように溶接線が環状の場合は終始端が存在せず、終始端で発生しやすい割れや異結晶の発生が抑制可能である。 Furthermore, by cooling the lower part of the gas turbine blade, a larger temperature gradient can be obtained, and solidification conditions that facilitate directional solidification can be obtained. In addition, since the weld line is always melted, when the weld line is annular as in this embodiment, there is no starting end, and it is possible to suppress the generation of cracks and different crystals that are likely to occur at the starting end.
本実施例ではシールドガスを用いていないが、パウダ供給部９にシールドガス供給機構を設けたり、別のガスノズルを用いたり、雰囲気置換したりすることで、より安定したシールドが得られる。 Although no shield gas is used in this embodiment, a more stable shield can be obtained by providing a shield gas supply mechanism in the powder supply unit 9, using another gas nozzle, or replacing the atmosphere.
また本実施例ではパウダ供給部９として２つの管状の部品を用いたが、形状はこれに限定されない。
また本実施例では溶加材にパウダを用いたが、溶加材の形状はこれに限定されない。
In this embodiment, two tubular parts are used as the powder supply unit 9, but the shape is not limited to this.
In this embodiment, powder is used as the filler material, but the shape of the filler material is not limited to this.
本実施例では、溶接線の溶融状態を保持する方法として半導体レーザを用いた例を述べる。図７に実施例３のレーザ肉盛装置の外観模式図を示す。本実施例ではガスタービン翼の補修を対象としている。１７は半導体レーザヘッド、１８はロボットアームを示している。図８に半導体レーザヘッドの内部構造を示す。１９は半導体レーザ発生部を示す。半導体レーザヘッド１７で生成されたレーザ４はガスタービン翼５に照射される。パウダフィーダ７からキャリアガスとともに送給されたパウダはパウダ供給部９を通じて、溶融池１０に送られる。半導体レーザヘッド１７は半導体レーザ発生部１９を２２個、溶接線形状に並べた構造となっており、溶接線と同じビーム形状を照射することが可能である。この半導体レーザヘッド１７を用いてレーザを照射し続けることで、溶接部が常に溶融している状態を保持した。 In this embodiment, an example in which a semiconductor laser is used as a method for maintaining the molten state of the weld line will be described. FIG. 7 is a schematic external view of the laser cladding apparatus according to the third embodiment. This embodiment is intended for repair of gas turbine blades. Reference numeral 17 denotes a semiconductor laser head, and 18 denotes a robot arm. FIG. 8 shows the internal structure of the semiconductor laser head. Reference numeral 19 denotes a semiconductor laser generator. The laser 4 generated by the semiconductor laser head 17 is applied to the gas turbine blade 5. The powder fed from the powder feeder 7 together with the carrier gas is sent to the molten pool 10 through the powder supply unit 9. The semiconductor laser head 17 has a structure in which 22 semiconductor laser generators 19 are arranged in a weld line shape, and can irradiate the same beam shape as the weld line. By continuing to irradiate the laser using this semiconductor laser head 17, the state where the welded part was always melted was maintained.
本実施例では溶接対象がガスタービン翼であるため、溶接線はガスタービン翼の上端の形状となる。本実施例では、パウダ供給部９は管状の部品を採用し、パウダフィーダ７から送給されたパウダを溶融池１０に吹き付けた。またパウダ供給部９はロボットアーム１８に固定した。またロボットアーム１８の動作はレーザ４とは独立しているため、パウダ供給部９の操作速度やパウダ供給量、パウダ供給位置を自由に調整することができる。 In this embodiment, since the object to be welded is a gas turbine blade, the weld line has the shape of the upper end of the gas turbine blade. In this embodiment, the powder supply unit 9 employs a tubular part, and the powder supplied from the powder feeder 7 is sprayed onto the molten pool 10. The powder supply unit 9 was fixed to the robot arm 18. Further, since the operation of the robot arm 18 is independent of the laser 4, the operation speed, the powder supply amount, and the powder supply position of the powder supply unit 9 can be freely adjusted.
本実施例でも、パウダ８が供給された分だけ肉盛部を形成することができ、肉盛部の表面を常に溶融させておくことができる。従って、熱流の方向とガスタービン翼の結晶の優先成長方向とが一致し、指向性凝固しやすい凝固条件となるので、ガスタービン翼と肉盛部との溶接部の割れを抑制することができる。またパウダ供給量を調整することで、成長速度を制御することが可能であり、指向性凝固しやすい凝固条件を得ることが可能となる。 Also in this embodiment, the build-up portion can be formed as much as the powder 8 is supplied, and the surface of the build-up portion can always be melted. Accordingly, the direction of heat flow matches the preferential growth direction of the crystal of the gas turbine blade, and the solidification conditions are likely to cause directional solidification, so that cracking of the welded portion between the gas turbine blade and the built-up portion can be suppressed. . Further, by adjusting the powder supply amount, it is possible to control the growth rate and to obtain a solidification condition that facilitates directional solidification.
さらにガスタービン翼の下部を冷却することによって、より大きな温度勾配を得ることができ、指向性凝固しやすい凝固条件を得ることが可能となる。また溶接線が常に溶融しているため、本実施例のように溶接線が環状の場合は終始端が存在せず、終始端で発生しやすい割れや異結晶の発生が抑制可能である。 Furthermore, by cooling the lower part of the gas turbine blade, a larger temperature gradient can be obtained, and solidification conditions that facilitate directional solidification can be obtained. In addition, since the weld line is always melted, when the weld line is annular as in this embodiment, there is no starting end, and it is possible to suppress the generation of cracks and different crystals that are likely to occur at the starting end.
本実施例ではシールドガスを用いていないが、パウダ供給部９にシールドガス供給機構を設けたり、別のガスノズルを用いたり、雰囲気置換したりすることで、より安定したシールドが得られる。 Although no shield gas is used in this embodiment, a more stable shield can be obtained by providing a shield gas supply mechanism in the powder supply unit 9, using another gas nozzle, or replacing the atmosphere.
また本実施例ではパウダ供給部９として２つの管状の部品を用いたが、形状はこれに限定されない。実施例１のようなパウダ供給部でもよい。
また本実施例では溶加材にパウダを用いたが、溶加材の形状はこれに限定されない。
In this embodiment, two tubular parts are used as the powder supply unit 9, but the shape is not limited to this. The powder supply unit as in the first embodiment may be used.
In this embodiment, powder is used as the filler material, but the shape of the filler material is not limited to this.
１ レーザ発振器
２ 光ファイバ
３ スキャナーヘッド（ヘッド）
４ レーザ
５ ガスタービン翼
６ 加工テーブル
７ パウダフィーダ
８ パウダ
９ パウダ供給部
１０ 溶融池
１１ パウダ供給部の保持部
１２ パウダ供給管
１３ パウダ導入口
１４Ａ レーザの進行方向（紙面手前方向）
１４Ｂ レーザの進行方向（紙面奥行方向）
１５ パウダ供給部の駆動部
１６ パウダ供給部のレール
１７ 半導体レーザヘッド（ヘッド）
１８ ロボットアーム
１９ 半導体レーザ発生部
1 Laser oscillator 2 Optical fiber 3 Scanner head (head)
4 Laser 5 Gas turbine blade 6 Processing table 7 Powder feeder 8 Powder 9 Powder supply unit 10 Molten pool 11 Powder supply unit holding unit 12 Powder supply pipe 13 Powder introduction port 14A Laser traveling direction (front side of paper)
14B Laser traveling direction (depth direction on paper)
15 Driving Unit of Powder Supply Unit 16 Rail 17 of Powder Supply Unit Semiconductor Laser Head (Head)
18 Robot arm 19 Semiconductor laser generator
Claims (8)
前記所定の施工対象物は方向凝固制御された結晶組織を有するガスタービン翼であり、前記表面は前記ガスタービン翼の上端部の環状表面であり、
前記環状表面にレーザを照射して環状の溶融池を形成するヘッドと、
前記環状の溶融池に溶加材を供給する溶加材供給部とを備え、
前記ヘッドは、溶接施工している間は前記環状の溶融池の全てが溶融状態を保持するように、前記環状表面に沿って前記レーザを走査させるミラー回転機構又は前記環状表面の全てに対して前記レーザを常に照射する半導体レーザ発生部を備え、
前記溶加材供給部は、供給した前記溶加材が溶融凝固して肉盛部を形成する際に該肉盛部の成長が前記ガスタービン翼の結晶組織の優先成長方向と一致した指向性凝固となるように、前記環状の溶融池に沿って均一に前記溶加材を供給し続ける構造又は機構を備えることを特徴とするレーザ肉盛溶接装置。 A laser overlay welding apparatus that performs overlay welding on the surface of a predetermined construction object,
The predetermined construction object is a gas turbine blade having a crystal structure controlled in direction solidification, and the surface is an annular surface of an upper end portion of the gas turbine blade,
A head for forming a molten pool of cyclic by irradiating Les chromatography The said annular surface,
Bei example a filler metal supply section for supplying a filler metal to the molten pool of said annular,
The head is against a mirror rotation mechanism that scans the laser along the annular surface or all of the annular surface so that all of the annular molten pool remains molten during welding . A semiconductor laser generator that constantly irradiates the laser;
The filler material supply unit has a directivity in which the growth of the build-up portion coincides with the preferential growth direction of the crystal structure of the gas turbine blade when the supplied melt material is melted and solidified to form the build-up portion. A laser overlay welding apparatus comprising a structure or a mechanism for continuously supplying the filler material uniformly along the annular molten pool so as to be solidified .
前記溶加材供給部の前記構造は、前記溶加材の出口の形状が前記ガスタービン翼上端部の前記環状表面と同じ形状になっており、当該出口が前記環状表面の上方に配置されていることを特徴とするレーザ肉盛溶接装置。 In the laser overlay welding apparatus according to claim 1 ,
The structure of the filler metal feeder, the shape of the outlet of the filler material has become the same shape as the gas turbine blade upper end said annular surface, is the outlet disposed above the annular surface Tei A laser overlay welding apparatus characterized by that.
前記溶加材供給部の前記機構は、前記溶加材のパウダを供給するパウダ供給部と、該パウダ供給部を走査駆動する駆動部と、該駆動部を乗せるレールとを備え、前記パウダ供給部が前記レール上を走査可能に構成されていることを特徴とするレーザ肉盛装置。 In the laser overlay welding apparatus according to claim 1 ,
Wherein the mechanism of filler metal feeder includes front Stories and powder for supplying powder supply portion of the filler material, a driving unit for scanning driving the powder supply part, and a rail to put the drive unit, the powder A laser build-up apparatus, wherein the supply unit is configured to be able to scan the rail .
前記ガスタービン翼の結晶組織の優先成長方向と反対方向にある前記ガスタービン翼の下部を冷却する機構を更に備えることを特徴とするレーザ肉盛溶接装置。A laser overlay welding apparatus, further comprising a mechanism for cooling a lower portion of the gas turbine blade in a direction opposite to a preferential growth direction of a crystal structure of the gas turbine blade.
前記所定の施工対象物は方向凝固制御された結晶組織を有するガスタービン翼であり、前記表面は前記ガスタービン翼の上端部の環状表面であり、
前記環状表面にレーザを照射して環状の溶融池を形成する工程と、
前記環状の溶融池に溶加材を供給する工程とを有し、
前記環状の溶融池を形成する工程は、溶接施工している間は前記環状の溶融池の全てが溶融状態を保持するように、前記環状の溶融池の凝固が完了する前に前記レーザを再照射する又は前記環状の溶融池の全てに対して前記レーザを常に照射する工程であり、
前記溶加材を供給する工程は、供給した前記溶加材が溶融凝固して肉盛部を形成する際に該肉盛部の成長が前記ガスタービン翼の結晶組織の優先成長方向と一致した指向性凝固となるように、前記環状の溶融池に沿って均一に前記溶加材を供給し続ける工程であることを特徴とする肉盛溶接部品の製造方法。 A method of manufacturing a predetermined execution object overlay welding parts was Les chromatography The overlay welding on the surface of,
The predetermined construction object is a gas turbine blade having a crystal structure controlled in direction solidification, and the surface is an annular surface of an upper end portion of the gas turbine blade,
Forming a molten pool of cyclic by irradiating Les chromatography The said annular surface,
Supplying a filler material to the annular molten pool,
The step of forming the annular molten pool is to re- energize the laser before solidification of the annular molten pool is completed so that all of the annular molten pool remains molten during welding. Irradiating or always irradiating the laser to all of the annular molten pool ,
In the step of supplying the filler material, when the supplied filler material is melted and solidified to form a buildup portion, the growth of the buildup portion coincided with the preferential growth direction of the crystal structure of the gas turbine blade. as the directional solidification method of the overlay welding parts it characterized in that the step of continuously supplying a uniform said filler material along a molten pool of said annular.
前記溶加材を供給する工程は、前記ガスタービン翼上端部の前記環状表面と同じ形状を有し該環状表面の上方に配置された溶加材供給機構から、前記溶加材を供給し続ける工程であることを特徴とする肉盛溶接部品の製造方法。 In the manufacturing method of overlay welding part according to claim 5,
The step of supplying the filler material continues to supply the filler material from a filler material supply mechanism that has the same shape as the annular surface of the upper end portion of the gas turbine blade and is disposed above the annular surface. method for producing overlay welding parts you being a process.
前記溶加材を供給する工程は、前記ガスタービン翼上端部の前記環状表面に沿って前記溶加材を供給するように走査可能に構成された溶加材供給機構から、前記溶加材を供給し続ける工程であることを特徴とする肉盛溶接部品の製造方法。 In the manufacturing method of overlay welding part according to claim 5,
Step of supplying the filler material from the scannable constructed filler material supply mechanism to supply the filler material along the annular surface of the gas turbine blade upper end, the filler material method for producing overlay welding parts you characterized in that the step of continuously supplying.
溶接施工している間、前記ガスタービン翼の結晶組織の優先成長方向と反対方向にある前記ガスタービン翼の下部を冷却する工程を更に有することを特徴とする肉盛溶接部品の製造方法。A method for manufacturing a built-up welded part, further comprising a step of cooling a lower portion of the gas turbine blade in a direction opposite to a preferential growth direction of a crystal structure of the gas turbine blade during welding.
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