WO2015068227A1 - Turbine blade and manufacturing method therefor - Google Patents
Turbine blade and manufacturing method therefor Download PDFInfo
- Publication number
- WO2015068227A1 WO2015068227A1 PCT/JP2013/080028 JP2013080028W WO2015068227A1 WO 2015068227 A1 WO2015068227 A1 WO 2015068227A1 JP 2013080028 W JP2013080028 W JP 2013080028W WO 2015068227 A1 WO2015068227 A1 WO 2015068227A1
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- Prior art keywords
- turbine blade
- shroud
- manufacturing
- metal powder
- contact portion
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/506—Hardness
Definitions
- the present invention relates to a turbine blade having a wear-resistant build-up on a shroud contact surface and a method for manufacturing the same.
- a shroud is formed at the blade tip (tip) of a turbine blade, and the shrouds of adjacent turbine blades are brought into contact with each other at a contact surface, thereby suppressing leakage of high-temperature combustion gas and vibration of the turbine blade. Is reduced.
- the contact surface between the shrouds needs to have wear resistance, but since the operating temperature of the turbine blade is high, the contact surface is required to have wear resistance at a particularly high temperature.
- An object of the present invention is to provide a turbine blade that suppresses cracks in the build-up on the shroud contact surface and a method for manufacturing the same.
- a turbine blade according to the present invention is a plurality of turbine blades arranged in a circumferential direction, and a shroud at the blade tip is in contact with an adjacent turbine blade,
- the contact portion is provided with a wear-resistant overlay made of a melt of metal powder by a high-density energy beam.
- a laser beam is used as the high-density energy beam, but an electron beam can also be used.
- the high-density energy beam since the high-density energy beam has excellent directivity and energy density, the shape accuracy of the metal powder build-up at the contact portion of the shroud is high, the wear resistance is excellent, and the hardness at high temperature is high. It becomes high, and it is possible to obtain a buildup that is homogeneous and excellent in durability without cracking.
- the directivity of the high-density energy beam is high, it is possible to build up stable quality even in a complicated shape such as a contact portion of the shroud.
- the metal powder is preferably made of a cobalt-based alloy. According to this configuration, since the cobalt-based alloy is excellent in heat resistance and wear resistance, the build-up using the cobalt-based alloy is excellent in heat resistance and wear resistance and can suppress generation of cracks.
- the cobalt base alloy is preferably stellite or trivalloy. According to this structure, stellite and trivalloy can simultaneously achieve wear resistance, corrosion resistance, and heat resistance environment among cobalt-based alloys, so the build-up at the contact portion of the shroud is more excellent in heat resistance and wear resistance, and cracking occurs. Can be more effectively suppressed.
- the base material of the shroud is preferably a nickel base alloy.
- the cobalt-based alloy containing stellite and trivalloy contains Ni in its chemical composition, and the shroud base material is extremely compatible with the nickel-based alloy.
- the adhesion density is high, the build-up is further solid, and the occurrence of cracks is further suppressed.
- a contact portion of a shroud at a blade tip that contacts an adjacent turbine blade is preheated to 200 ° C. or more and below the aging temperature of the base material of the shroud, and then a high-density energy beam is applied.
- a high-density energy beam is applied.
- the metal powder and the contact portion are melted by heat of a high-density energy beam to form the overlay.
- a laser beam is used as the high-density energy beam, but an electron beam can also be used.
- the contact portion of the shroud is preheated to 200 ° C. or more and below the aging temperature of the shroud base material before irradiation with the high-density energy beam. There is little temperature gap at the contact area when irradiating with a density energy beam. Thereby, generation
- after-heating is applied at 350 ° C. or higher to perform soaking.
- the temperature drop of the build-up portion proceeds over time. As a result, the temperature of the build-up does not drop sharply, and the occurrence of cracks is further suppressed.
- FIG. 1 is a perspective view of a turbine blade according to a preferred embodiment of the present invention. It is a perspective view which shows the buildup part which is the principal part of the same turbine blade. It is a schematic diagram which shows the manufacturing method of the turbine blade by laser irradiation.
- a turbine blade 1 of a gas turbine has a blade portion 2 attached to a turbine disk 4 via a base attachment portion 3, and a shroud 5 is provided at the blade tip.
- a plurality of turbine blades 1 are arranged in the circumferential direction P of the turbine disk 4.
- the shroud 5 is in contact with the shroud 5 of the adjacent turbine blade 1, and as shown in FIG. Abrasive build-up 7 is applied.
- the outer surface of the build-up 7 becomes a contact surface 5aa that contacts the shroud 5 of the adjacent turbine blade 1.
- the contact portion 5 a is located at the center portion in the turbine axial direction C on both sides of the shroud 5 and is inclined with respect to the turbine axial direction C.
- the front and rear side portions 5b and 5c of the contact portion 5a forming the central side portion of the shroud 5 are substantially parallel to the axial direction C. Therefore, the side portions 5a to 5c of the shroud 5 are bent and have complicated shapes. It has become.
- the shroud 5 is formed of a heat resistant alloy having a nickel base alloy (for example, Mar-M247 (trade name) or Inconel-713C (trade name)) as a base material.
- a nickel base alloy for example, Mar-M247 (trade name) or Inconel-713C (trade name)
- a cobalt-based alloy is used, and in detail, Stellite (trade name) or Tribaloy (trade name).
- Stellite 6, 12, 694, 720 is used as Stellite
- Trivalloy T-800, T-400, T-900 is used as Triballoy.
- the chemical composition of Stellite 6 is Cr 26-32%, W 3-6%, Fe ⁇ 3%, Mo ⁇ 1%, Ni ⁇ 3%, C 0.9-1.4%, Si ⁇ 2%, Mn ⁇ 1 %, Balance Co.
- the chemical composition of Trivalloy T-800 is C0.04%, Cr17.4%, Ni0.8%, Co; Bal, Mo28.2%, Si3.4%.
- the contact portion 5a of the blade shroud 5 is 200 ° C. or higher, preferably 500 ° C. or higher, and the aging temperature of the base material (nickel-based alloy) of the shroud 5 (Mar-M247: 870 ° C./Inconel- 713C: 760 ° C.) or less.
- the preheating time is 5 to 10 minutes.
- FIG. 3 schematically shows the LMD method.
- the nozzle 10 has a double tube structure of an inner tube 10a in the center and an outer tube 5b provided on the outer periphery thereof.
- a laser beam LB from a beam generation source (not shown) is applied to the contact portion 5a of the shroud 5 as the work W from the inner tube 10a.
- a shield gas (argon gas) SG is injected as indicated by an arrow.
- Trivalloy T-800 which is the metal powder 6, is injected from the outer tube 10b toward the irradiation region (contact portion 5a) of the laser beam LB indicated by a broken line.
- the shroud base material (nickel-based alloy) 11 under the Trivalloy T-800 build-up is melted by the laser beam LB, and the Trivalloy T-800 build-up 7 is formed on the melted base material 11. It is formed.
- the thickness T of the overlay 7 is about 3 mm.
- post-heating is applied to the build-up 7 at 350 ° C. or higher, and a soaking process is performed to make the temperature of the build-up 7 uniform.
- the post-heating temperature is 500 to 600 ° C.
- the post-heating time is 20 minutes or longer, for example, 20 to 40 minutes. Cool gradually after post-heating. Note that the post-heat treatment in the third stage is not necessarily required.
- Trivalloy T-400, T-800, T-900, Stellite 6, 12, 694, 720 such as Stellite have a sufficiently high HRC hardness of 54 or higher up to a high temperature of 800 ° C. Therefore, it is speculated that all of the trivalloy and stellite systems exhibiting this level of HRC hardness can be used as the material for the build-up 7 having excellent wear resistance according to the present invention.
- the wear-resistant build-up 7 of the metal powder 6 applied to the contact portion 5a of the shroud 5 shown in FIG. 2 is excellent in directivity and energy density of the laser, so that the contact portion 5a of the shroud 5 is used.
- the shape 7 of the build-up 7 of the metal powder 6 is high, the wear resistance is excellent, the hardness at high temperature is high, it is homogeneous and does not generate cracks, and is excellent in durability.
- the directivity of the laser beam LB is high, a stable quality overlay 7 can be formed even in a complicated shape such as the contact portion 5a of the shroud 5.
- the build-up 7 in the contact portion 5a of the shroud 5 using this is excellent in heat resistance and wear resistance and generation of cracks. Can be suppressed.
- the build-up 7 in the contact portion 5a has more heat resistance and wear resistance. It is excellent and can suppress the generation of cracks more effectively.
- the cobalt-based alloy containing stellite and trivalloy used to form the overlay 7 contains Ni in its chemical composition and is extremely compatible with the nickel-based alloy of the base material of the shroud 5.
- the contact density at the contact portion 5a is high, and the build-up 7 is more robust and the occurrence of cracks is further suppressed.
- the contact portion 5a of the shroud 5 is preheated to 200 ° C. or more and lower than the aging temperature of the base material of the shroud 5, and thereafter, the contact portion 5a of the shroud 5 is applied to the contact portion 5a. Since the metal powder 6 and the contact portion 5a are melted by irradiation with the laser shown in FIG. 3 to form the build-up 7, the temperature at the contact portion 5a at the time of laser irradiation with the base material of the shroud 5 is compared with the case where preheating is not performed. There are few gaps. Thereby, generation
- a laser is used as the high-density energy beam, but the present invention is not limited to this.
- An electron beam may be used as the high-density energy beam.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laser Beam Processing (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
The present invention provides a turbine blade, and a manufacturing method therefor, for which the durability of a thick section at a shroud contact part is improved. A plurality of turbine blades (1) are disposed lined up in the circumferential direction, and blade-end shrouds (5) make contact between adjacent turbine blades (1). At a contact section (5a) of the shroud, provided is a thick section (7) having abrasion resistance and formed of the product that results from melting metal powder (6) with a high-density energy beam. The metal powder (6) is, for example, Stellite or Triballoy, which are cobalt base alloys.
Description
本発明は、シュラウドの接触面に耐摩耗性の肉盛りが施されたタービン翼およびその製造方法に関する。
The present invention relates to a turbine blade having a wear-resistant build-up on a shroud contact surface and a method for manufacturing the same.
従来、ガスタービンエンジンではタービン翼の翼端（先端）にシュラウドを形成し、隣接するタービン翼のシュラウド同士を接触面で接触させることにより、高温の燃焼ガスの漏れを抑えるとともに、タービン翼の振動を低減させている。シュラウド同士の接触面は耐摩耗性が必要となるが、タービン翼の使用温度は高温であるため、接触面には特に高温での耐摩耗性が要求される。
Conventionally, in a gas turbine engine, a shroud is formed at the blade tip (tip) of a turbine blade, and the shrouds of adjacent turbine blades are brought into contact with each other at a contact surface, thereby suppressing leakage of high-temperature combustion gas and vibration of the turbine blade. Is reduced. The contact surface between the shrouds needs to have wear resistance, but since the operating temperature of the turbine blade is high, the contact surface is required to have wear resistance at a particularly high temperature.
ガスタービンの高効率化に伴い、タービン翼の使用環境は高温になる。また、ガスタービンが幅広い回転数もしくは出力範囲で使用される場合、接触面はより激しい摩耗を来たすと考えられる。このような厳しい使用環境に対応するために、接触面の形成には高温での耐摩耗性に優れる材料の使用が求められる。例えば、コバルト基合金のような耐摩耗性材料を、ＴＩＧ溶接やプラズマ溶接によって接触面に肉盛りする方法がある（例えば特許文献１，２）。
As the efficiency of gas turbines increases, the usage environment of turbine blades becomes high. In addition, when the gas turbine is used in a wide range of rotation speeds or power ranges, the contact surface is considered to cause more severe wear. In order to cope with such a severe use environment, the formation of the contact surface requires the use of a material having excellent wear resistance at high temperatures. For example, there is a method of depositing a wear-resistant material such as a cobalt-based alloy on the contact surface by TIG welding or plasma welding (for example, Patent Documents 1 and 2).
しかしながら、このような接触面形成方法による場合、入熱が大きいため、シュラウド接触面の肉盛り部分に熱応力の増加に起因する割れが発生しやすい。そして、その割れは、使用環境がきわめて厳しいために、進展しやすいものとなる。また、大きい入熱のため、シュラウドの母材のひずみも大きくなり、求められる製品形状から大きく外れる傾向があった。さらに、シュラウドの接触面のような複雑な形状をＴＩＧ溶接やプラズマ溶接で施工する場合、ワークであるタービン翼と加工ヘッドの距離の取り方が難しいために接触面への安定した品質の肉盛りが難しい。
However, according to such a contact surface forming method, since heat input is large, cracks due to an increase in thermal stress are likely to occur in the built-up portion of the shroud contact surface. And the crack becomes easy to progress because use environment is very severe. Further, due to the large heat input, the distortion of the shroud base material also increased, and there was a tendency to deviate greatly from the required product shape. Furthermore, when a complex shape such as a shroud contact surface is to be constructed by TIG welding or plasma welding, it is difficult to determine the distance between the turbine blade, which is the workpiece, and the machining head. Is difficult.
本発明の目的は、シュラウド接触面での肉盛りにおける割れを抑制したタービン翼およびその製造方法を提供することにある。
An object of the present invention is to provide a turbine blade that suppresses cracks in the build-up on the shroud contact surface and a method for manufacturing the same.
前記目的を達成するために、本発明に係るタービン翼は、周方向に並べて複数個が配置されるタービン翼であって、隣接するタービン翼との間で翼端のシュラウドが接触しており、その接触部に、高密度エネルギービームによる金属粉末の溶融物からなる耐摩耗性の肉盛りが施されている。高密度エネルギービームとしては、例えばレーザビームが使用されるが、電子ビームを使用することもできる。
In order to achieve the above object, a turbine blade according to the present invention is a plurality of turbine blades arranged in a circumferential direction, and a shroud at the blade tip is in contact with an adjacent turbine blade, The contact portion is provided with a wear-resistant overlay made of a melt of metal powder by a high-density energy beam. For example, a laser beam is used as the high-density energy beam, but an electron beam can also be used.
この構成によれば、高密度エネルギービームは指向性、エネルギー密度に優れているため、シュラウドの接触部における金属粉末の肉盛りの形状精度が高く、耐摩耗性に優れ、かつ高温での硬度が高くなり、均質で割れの発生のない耐久性に優れた肉盛りが得られる。また、高密度エネルギービームの指向性が高いことから、シュラウドの接触部のような複雑な形状にも、安定した品質の肉盛りができる。
According to this configuration, since the high-density energy beam has excellent directivity and energy density, the shape accuracy of the metal powder build-up at the contact portion of the shroud is high, the wear resistance is excellent, and the hardness at high temperature is high. It becomes high, and it is possible to obtain a buildup that is homogeneous and excellent in durability without cracking. In addition, since the directivity of the high-density energy beam is high, it is possible to build up stable quality even in a complicated shape such as a contact portion of the shroud.
本発明のタービン翼において、前記金属粉末はコバルト基合金からなることが好ましい。この構成によれば、コバルト基合金は、耐熱性および耐摩耗性に優れるため、これを用いた肉盛りは，耐熱性および耐摩耗性に優れ、かつ割れの発生を抑制できる。
In the turbine blade of the present invention, the metal powder is preferably made of a cobalt-based alloy. According to this configuration, since the cobalt-based alloy is excellent in heat resistance and wear resistance, the build-up using the cobalt-based alloy is excellent in heat resistance and wear resistance and can suppress generation of cracks.
本発明のタービン翼において、前記コバルト基合金はステライトまたはトリバロイであることが好ましい。この構成によれば、ステライトおよびトリバロイはコバルト基合金類の中でも耐摩耗、耐食、耐熱環境を同時に実現できるので、シュラウドの接触部における肉盛りは耐熱性および耐摩耗性が一層優れ、割れの発生を一層効果的に抑制できる。
In the turbine blade of the present invention, the cobalt base alloy is preferably stellite or trivalloy. According to this structure, stellite and trivalloy can simultaneously achieve wear resistance, corrosion resistance, and heat resistance environment among cobalt-based alloys, so the build-up at the contact portion of the shroud is more excellent in heat resistance and wear resistance, and cracking occurs. Can be more effectively suppressed.
本発明のタービン翼において、前記シュラウドの母材はニッケル基合金であることが好ましい。この構成によれば、ステライトおよびトリバロイを含むコバルト基合金は、その化学組成中にＮｉを含んでおり、シュラウドの母材はニッケル基合金との相溶性が極めて高いことから、シュラウドの母材との密着密度が高く、肉盛りは一層堅牢となって、割れの発生がより一層抑制される。
In the turbine blade of the present invention, the base material of the shroud is preferably a nickel base alloy. According to this configuration, the cobalt-based alloy containing stellite and trivalloy contains Ni in its chemical composition, and the shroud base material is extremely compatible with the nickel-based alloy. The adhesion density is high, the build-up is further solid, and the occurrence of cracks is further suppressed.
本発明に係るタービン翼を製造する方法は、隣接するタービン翼と接触する翼端のシュラウドの接触部を、２００℃以上でシュラウドの母材の時効温度以下に予熱したのち、高密度エネルギービームを前記接触部に照射し、その照射領域に金属粉末を噴射することにより、高密度エネルギービームの熱で前記金属粉末および前記接触部を溶融させて前記肉盛りを形成する。高密度エネルギービームとしては、例えばレーザビームが使用されるが、電子ビームを使用することもできる。
In the method of manufacturing a turbine blade according to the present invention, a contact portion of a shroud at a blade tip that contacts an adjacent turbine blade is preheated to 200 ° C. or more and below the aging temperature of the base material of the shroud, and then a high-density energy beam is applied. By irradiating the contact portion and injecting metal powder onto the irradiated region, the metal powder and the contact portion are melted by heat of a high-density energy beam to form the overlay. For example, a laser beam is used as the high-density energy beam, but an electron beam can also be used.
この構成によれば、高密度エネルギービームの照射前に、シュラウドの接触部を、２００℃以上でシュラウドの母材の時効温度以下に予熱するので、予熱しない場合に比べ、シュラウドの母材と高密度エネルギービーム照射時の接触部での温度ギャップが少ない。これにより、肉盛りでの割れの発生を抑制できる。
According to this configuration, the contact portion of the shroud is preheated to 200 ° C. or more and below the aging temperature of the shroud base material before irradiation with the high-density energy beam. There is little temperature gap at the contact area when irradiating with a density energy beam. Thereby, generation | occurrence | production of the crack by the buildup can be suppressed.
本発明に係るタービン翼を製造する方法において、前記肉盛りの形成後に３５０℃以上で後熱を加え均熱処理を行うことが好ましい。この構成によれば、後熱を行わない場合に比べ、肉盛り部分の温度低下が時間をかけて進むことになる。これにより、肉盛りは急激に温度低下しないことから、割れの発生が一層抑制される。
In the method of manufacturing a turbine blade according to the present invention, it is preferable that after the formation of the build-up, after-heating is applied at 350 ° C. or higher to perform soaking. According to this structure, compared with the case where after-heating is not performed, the temperature drop of the build-up portion proceeds over time. As a result, the temperature of the build-up does not drop sharply, and the occurrence of cracks is further suppressed.
請求の範囲および／または明細書および／または図面に開示された少なくとも２つの構成のどのような組合せも、本発明に含まれる。特に、請求の範囲の各請求項の２つ以上のどのような組合せも、本発明に含まれる。
Any combination of at least two configurations disclosed in the claims and / or the specification and / or drawings is included in the present invention. In particular, any combination of two or more of each claim in the claims is included in the present invention.
本発明は、添付の図面を参考にした以下の好適な実施形態の説明から、より明瞭に理解されるであろう。しかしながら、実施形態および図面は単なる図示および説明のためのものであり、本発明の範囲を定しめるために利用されるべきものではない。本発明の範囲は添付の請求の範囲によって定まる。添付図面において、複数の図面における同一の符号は、同一または相当する部分を示す。
本発明の好ましい実施形態にかかるタービン翼の斜視図である。
同タービン翼の要部である肉盛り部分を示す斜視図である。
レーザ照射によるタービン翼の製造方法を示す模式図である。
The present invention will be understood more clearly from the following description of preferred embodiments with reference to the accompanying drawings. However, the embodiments and drawings are merely for illustration and description, and should not be used to define the scope of the present invention. The scope of the invention is defined by the appended claims. In the accompanying drawings, the same reference numerals in a plurality of drawings indicate the same or corresponding parts.
1 is a perspective view of a turbine blade according to a preferred embodiment of the present invention. It is a perspective view which shows the buildup part which is the principal part of the same turbine blade. It is a schematic diagram which shows the manufacturing method of the turbine blade by laser irradiation.
以下、本発明の好ましい実施形態について図１および図２を参照しながら説明する。図１に示すように、ガスタービンのタービン翼１は、翼部２が根元の取付部３を介してタービンディスク４に取り付けられ、その翼端にはシュラウド５が設けられている。タービン翼１はタービンディスク４の周方向Ｐに並べて複数個が配置されている。シュラウド５は、隣接するタービン翼１のシュラウド５との間で接触しており、その接触部５ａに、図２に示すように、高密度エネルギービームの一種であるレーザの照射による金属粉末の耐摩耗性の肉盛り７が施されている。この肉盛り７の外側面が隣接するタービン翼１のシュラウド５と接触する接触面５ａａとなる。接触部５ａはシュラウド５の両側部におけるタービン軸心方向Ｃの中央部に位置しており、タービン軸心方向Ｃに対して傾斜している。シュラウド５における中央の側部を形成する接触部５ａの前後両側部５ｂ、５ｃは、軸心方向Ｃにほぼ平行であり、したがって、シュラウド５の側部５ａ～５ｃは、曲折した複雑な形状となっている。
Hereinafter, a preferred embodiment of the present invention will be described with reference to FIG. 1 and FIG. As shown in FIG. 1, a turbine blade 1 of a gas turbine has a blade portion 2 attached to a turbine disk 4 via a base attachment portion 3, and a shroud 5 is provided at the blade tip. A plurality of turbine blades 1 are arranged in the circumferential direction P of the turbine disk 4. As shown in FIG. 2, the shroud 5 is in contact with the shroud 5 of the adjacent turbine blade 1, and as shown in FIG. Abrasive build-up 7 is applied. The outer surface of the build-up 7 becomes a contact surface 5aa that contacts the shroud 5 of the adjacent turbine blade 1. The contact portion 5 a is located at the center portion in the turbine axial direction C on both sides of the shroud 5 and is inclined with respect to the turbine axial direction C. The front and rear side portions 5b and 5c of the contact portion 5a forming the central side portion of the shroud 5 are substantially parallel to the axial direction C. Therefore, the side portions 5a to 5c of the shroud 5 are bent and have complicated shapes. It has become.
ここで、シュラウド５は、ニッケル基合金（例えば、Ｍａｒ－Ｍ２４７(商品名)やＩｎｃｏｎｅｌ－７１３Ｃ（商品名））を母材とする耐熱性合金で形成されている。シュラウド５の接触部５ａにレーザ照射により肉盛りされる耐摩耗性の金属粉末６としては、コバルト基合金を使用し、詳しくは、ステライト（Stellite（商品名））やトリバロイ（Tribaloy（商品名））を使用する。例えば、ステライトとしては、ステライト６，１２、６９４、７２０を用い、トリバロイとしては、トリバロイＴ－８００、Ｔ－４００、Ｔ－９００を用いる。ステライト６の化学組成は、Ｃｒ２６～３２％、Ｗ３～６％、Ｆｅ＜３％、Ｍｏ＜１％、Ｎｉ＜３％、Ｃ ０．９～１．４％、Ｓｉ＜２％、Ｍｎ＜１％、残部Ｃｏである。トリバロイＴ－８００の化学組成は、Ｃ０．０４％、Ｃｒ１７．４％、Ｎｉ０．８％、Ｃｏ；Ｂａｌ、Ｍｏ２８．２％、Ｓｉ３．４％である。
Here, the shroud 5 is formed of a heat resistant alloy having a nickel base alloy (for example, Mar-M247 (trade name) or Inconel-713C (trade name)) as a base material. As the wear-resistant metal powder 6 that is built up on the contact portion 5a of the shroud 5 by laser irradiation, a cobalt-based alloy is used, and in detail, Stellite (trade name) or Tribaloy (trade name). ). For example, Stellite 6, 12, 694, 720 is used as Stellite, and Trivalloy T-800, T-400, T-900 is used as Triballoy. The chemical composition of Stellite 6 is Cr 26-32%, W 3-6%, Fe <3%, Mo <1%, Ni <3%, C 0.9-1.4%, Si <2%, Mn <1 %, Balance Co. The chemical composition of Trivalloy T-800 is C0.04%, Cr17.4%, Ni0.8%, Co; Bal, Mo28.2%, Si3.4%.
つぎに、タービン翼１の製造方法の一例について説明する。第１段階では、翼端のシュラウド５の接触部５ａを、２００℃以上、好ましくは５００℃以上で、シュラウド５の母材（ニッケル基合金）の時効温度（Ｍａｒ－Ｍ２４７：８７０℃ / Ｉｎｃｏｎｅｌ－７１３Ｃ：７６０℃）以下に予熱する。予熱時間は５～１０分である。
Next, an example of a method for manufacturing the turbine blade 1 will be described. In the first stage, the contact portion 5a of the blade shroud 5 is 200 ° C. or higher, preferably 500 ° C. or higher, and the aging temperature of the base material (nickel-based alloy) of the shroud 5 (Mar-M247: 870 ° C./Inconel- 713C: 760 ° C.) or less. The preheating time is 5 to 10 minutes.
第２段階では、ＬＭＤ法（laser metal deposition）により、シュラウド５の接触部５ａに、耐摩耗性金属粉末６として、トリバロイＴ－８００を用いて肉盛りを形成する。図３はＬＭＤ法を模式的に示す。同図に示すように、ノズル１０は中央部の内管１０ａとその外周囲に設けられた外管５ｂの二重管構造になっている。内管１０ａから図示しないビーム発生源からのレーザビームＬＢがワークＷであるシュラウド５の接触部５ａに照射される。このとき、レーザビームＬＢの照射と同時に、シールドガス（アルゴンガス）ＳＧが矢印で示すように噴射される。
In the second stage, a build-up is formed on the contact portion 5a of the shroud 5 using triballoy T-800 as the wear-resistant metal powder 6 by the LMD method (laser metal deposition). FIG. 3 schematically shows the LMD method. As shown in the figure, the nozzle 10 has a double tube structure of an inner tube 10a in the center and an outer tube 5b provided on the outer periphery thereof. A laser beam LB from a beam generation source (not shown) is applied to the contact portion 5a of the shroud 5 as the work W from the inner tube 10a. At this time, simultaneously with the irradiation of the laser beam LB, a shield gas (argon gas) SG is injected as indicated by an arrow.
つづいて、外管１０ｂから金属粉末６であるトリバロイＴ－８００を、破線で示すレーザビームＬＢの照射領域（接触部５ａ）に向けて噴射する。このトリバロイＴ－８００の肉盛りの下にあるシュラウドの母材（ニッケル基合金）１１は、レーザビームＬＢにより溶融され、この溶融された母材１１の上にトリバロイＴ－８００の肉盛り７が形成される。肉盛り７の厚さＴは、３ｍｍ程度である。
Subsequently, Trivalloy T-800, which is the metal powder 6, is injected from the outer tube 10b toward the irradiation region (contact portion 5a) of the laser beam LB indicated by a broken line. The shroud base material (nickel-based alloy) 11 under the Trivalloy T-800 build-up is melted by the laser beam LB, and the Trivalloy T-800 build-up 7 is formed on the melted base material 11. It is formed. The thickness T of the overlay 7 is about 3 mm.
第３段階では、接触部５ａに所定の肉盛り７が形成された後に、この肉盛り７に対して３５０℃以上で後熱を加え、肉盛り７全体の温度を均一化する均熱処理を行う。より好ましくは、後熱温度は５００～６００℃、後熱時間は２０分以上、例えば２０～４０分の範囲である。後熱後には徐々に冷却する。なお、この第３段階の後熱処理は必ずしもなくてもよい。
In the third stage, after the predetermined build-up 7 is formed on the contact portion 5a, post-heating is applied to the build-up 7 at 350 ° C. or higher, and a soaking process is performed to make the temperature of the build-up 7 uniform. . More preferably, the post-heating temperature is 500 to 600 ° C., and the post-heating time is 20 minutes or longer, for example, 20 to 40 minutes. Cool gradually after post-heating. Note that the post-heat treatment in the third stage is not necessarily required.
トリバロイT－４００、T－８００、T－９００、ステライト６、１２、６９４、７２０のようなトリバロイ系、ステライト系は８００℃の高温までＨＲＣ硬度が５４以上と十分に高い。したがって、この程度のＨＲＣ硬度を示すトリバロイ系、ステライト系はすべて、本発明の耐摩耗性に優れた肉盛り７の材料として使用できると推察される。
Trivalloy T-400, T-800, T-900, Stellite 6, 12, 694, 720 such as Stellite have a sufficiently high HRC hardness of 54 or higher up to a high temperature of 800 ° C. Therefore, it is speculated that all of the trivalloy and stellite systems exhibiting this level of HRC hardness can be used as the material for the build-up 7 having excellent wear resistance according to the present invention.
以上説明したとおり、図２に示すシュラウド５の接触部５ａに施した金属粉末６の耐摩耗性の肉盛り７は、レーザが指向性、エネルギー密度に優れているため、シュラウド５の接触部５ａにおける金属粉末６の肉盛り７の形状精度が高く、耐摩耗性に優れ、かつ高温での硬度が高くなり、均質で割れの発生もなく、耐久性に優れている。また、レーザビームＬＢの指向性が高いことから、シュラウド５の接触部５ａのような複雑な形状にも、安定した品質の肉盛り７ができる。
As described above, the wear-resistant build-up 7 of the metal powder 6 applied to the contact portion 5a of the shroud 5 shown in FIG. 2 is excellent in directivity and energy density of the laser, so that the contact portion 5a of the shroud 5 is used. The shape 7 of the build-up 7 of the metal powder 6 is high, the wear resistance is excellent, the hardness at high temperature is high, it is homogeneous and does not generate cracks, and is excellent in durability. In addition, since the directivity of the laser beam LB is high, a stable quality overlay 7 can be formed even in a complicated shape such as the contact portion 5a of the shroud 5.
金属粉末６として耐熱性および耐摩耗性に優れたコバルト基合金を用いたので、これを用いた、シュラウド５の接触部５ａにおける肉盛り７は、耐熱性および耐摩耗性に優れ、割れの発生を抑制できる。
Since the cobalt-based alloy having excellent heat resistance and wear resistance is used as the metal powder 6, the build-up 7 in the contact portion 5a of the shroud 5 using this is excellent in heat resistance and wear resistance and generation of cracks. Can be suppressed.
コバルト基合金として用いたステライトおよびトリバロイは、コバルト基合金類の中でも優れた耐摩耗性、耐食性および耐熱性を同時に実現できるので、接触部５ａにおける肉盛り７は、耐熱性および耐摩耗性が一層優れ、割れの発生を一層効果的に抑制できる。
Since the stellite and trivalloy used as the cobalt-based alloy can simultaneously achieve excellent wear resistance, corrosion resistance and heat resistance among the cobalt-based alloys, the build-up 7 in the contact portion 5a has more heat resistance and wear resistance. It is excellent and can suppress the generation of cracks more effectively.
肉盛り７の形成に用いたステライトおよびトリバロイを含むコバルト基合金は、その化学組成中にＮｉを含んでおり、シュラウド５の母材のニッケル基合金との相溶性がきわめてよいから、シュラウド５の接触部５ａでの密着密度が高く、肉盛り７は一層堅牢となって割れの発生がより一層抑制される。
The cobalt-based alloy containing stellite and trivalloy used to form the overlay 7 contains Ni in its chemical composition and is extremely compatible with the nickel-based alloy of the base material of the shroud 5. The contact density at the contact portion 5a is high, and the build-up 7 is more robust and the occurrence of cracks is further suppressed.
タービン翼１を製造する方法において、レーザの照射前に、シュラウド５の接触部５ａを、２００℃以上でシュラウド５の母材の時効温度以下に予熱し、その後に、シュラウド５の接触部５ａに図３に示すレーザを照射して金属粉末６および接触部５ａを溶融させて肉盛り７を形成したので、予熱しない場合に比べ、シュラウド５の母材とレーザ照射時の接触部５ａでの温度ギャップが少ない。これにより、肉盛り７での割れの発生を抑制できる。
In the method of manufacturing the turbine blade 1, before the laser irradiation, the contact portion 5a of the shroud 5 is preheated to 200 ° C. or more and lower than the aging temperature of the base material of the shroud 5, and thereafter, the contact portion 5a of the shroud 5 is applied to the contact portion 5a. Since the metal powder 6 and the contact portion 5a are melted by irradiation with the laser shown in FIG. 3 to form the build-up 7, the temperature at the contact portion 5a at the time of laser irradiation with the base material of the shroud 5 is compared with the case where preheating is not performed. There are few gaps. Thereby, generation | occurrence | production of the crack in the overlay 7 can be suppressed.
また、前記肉盛り７の形成後に、３５０℃以上で後熱を加え均熱処理を行ったので、後熱を行わない場合に比べ、時間をかけて温度低下がすすみ、肉盛り７を急激に温度低下させることがないから、肉盛り７での割れの発生を一層抑制できる。
Further, after the formation of the build-up 7, post-heating was performed at 350 ° C. or higher, so that the temperature decreased over time as compared with the case where no post-heating was performed, and the build-up 7 was rapidly heated. Since it does not reduce, the generation | occurrence | production of the crack in the build-up 7 can be suppressed further.
以上のとおり、図面を参照しながら好適な実施形態および応用形態を説明したが、当業者であれば、本件明細書を見て、自明な範囲内で種々の変更および修正を容易に想定するであろう。したがって、そのような変更および修正は、請求の範囲から定まる本発明の範囲内のものと解釈される。例えば、上述の実施形態では、高密度エネルギービームとしてレーザを使用しているが、これに限定されない。高密度エネルギービームとして、電子ビームを使用してもよい。
As described above, the preferred embodiments and applications have been described with reference to the drawings. However, those skilled in the art can easily assume various changes and modifications within the obvious range by looking at the present specification. I will. Accordingly, such changes and modifications are to be construed as within the scope of the present invention as defined by the claims. For example, in the above-described embodiment, a laser is used as the high-density energy beam, but the present invention is not limited to this. An electron beam may be used as the high-density energy beam.
１…タービン翼
２…翼部
３…取付部
４…タービンディスク
５…シュラウド
５ａ…接触部
６…金属粉末
７…肉盛り
１０…ノズル
ＬＢ…レーザビーム
ＳＧ…シールドガス（アルゴンガス） DESCRIPTION OFSYMBOLS 1 ... Turbine blade 2 ... Blade | wing part 3 ... Mounting part 4 ... Turbine disk 5 ... Shroud 5a ... Contact part 6 ... Metal powder 7 ... Overlay 10 ... Nozzle LB ... Laser beam SG ... Shielding gas (argon gas)
２…翼部
３…取付部
４…タービンディスク
５…シュラウド
５ａ…接触部
６…金属粉末
７…肉盛り
１０…ノズル
ＬＢ…レーザビーム
ＳＧ…シールドガス（アルゴンガス） DESCRIPTION OF
Claims (11)
- 周方向に並べて複数個が配置されるタービン翼であって、
隣接するタービン翼との間で翼端のシュラウドが接触しており、
その接触部に、金属粉末の高密度エネルギービームによる溶融物からなる耐摩耗性の肉盛りが施されているタービン翼。 A plurality of turbine blades arranged side by side in the circumferential direction,
The blade shroud is in contact with the adjacent turbine blade,
A turbine blade having a wear-resistant buildup made of a melt of a metal powder with a high-density energy beam at its contact portion. - 請求項１に記載のタービン翼において、前記高密度エネルギービームはレーザビームであるタービン翼。 The turbine blade according to claim 1, wherein the high-density energy beam is a laser beam.
- 請求項１または２に記載のタービン翼において、前記金属粉末はコバルト基合金からなるタービン翼。 3. The turbine blade according to claim 1 or 2, wherein the metal powder is made of a cobalt-based alloy.
- 請求項３に記載のタービン翼において、前記コバルト基合金はステライトまたはトリバロイであるタービン翼。 4. The turbine blade according to claim 3, wherein the cobalt-based alloy is stellite or trivalloy.
- 請求項１から４のいずれか一項に記載のタービン翼おいて、前記シュラウドの母材はニッケル基合金であるタービン翼。 The turbine blade according to any one of claims 1 to 4, wherein a base material of the shroud is a nickel base alloy.
- 請求項１に記載のタービン翼を製造する方法であって、隣接するタービン翼と接触する翼端のシュラウドの接触部を、２００℃以上でシュラウドの母材の時効温度以下に予熱したのち、高密度エネルギービームを前記接触部に照射し、その照射領域に金属粉末を噴射することにより、前記高密度エネルギービームの熱で前記金属粉末および前記接触部を溶融させて前記肉盛りを形成するタービン翼の製造方法。 A method of manufacturing a turbine blade according to claim 1, wherein a contact portion of a shroud at a blade tip that is in contact with an adjacent turbine blade is preheated to 200 ° C or higher and lower than an aging temperature of a base material of the shroud. A turbine blade that forms the build-up by irradiating the contact portion with a density energy beam and injecting metal powder onto the irradiated region to melt the metal powder and the contact portion with the heat of the high-density energy beam. Manufacturing method.
- 請求項６に記載のタービン翼の製造方法において、前記高密度エネルギービームとしてレーザビームを使用するタービン翼の製造方法。 The method for manufacturing a turbine blade according to claim 6, wherein a laser beam is used as the high-density energy beam.
- 請求項６または７に記載のタービン翼を製造する方法において、前記肉盛りの形成後に３５０℃以上で後熱を加えて均熱処理を行うタービン翼の製造方法。 The method for manufacturing a turbine blade according to claim 6 or 7, wherein after the formation of the build-up, a soaking process is performed by applying post-heating at 350 ° C or higher.
- 請求項６から８のいずれか一項に記載のタービン翼を製造する方法において、前記金属粉末はコバルト基合金であるタービン翼の製造方法。 The method for manufacturing a turbine blade according to any one of claims 6 to 8, wherein the metal powder is a cobalt-based alloy.
- 請求項９に記載のタービン翼を製造する方法において、前記コバルト基合金はステライトまたはトリバロイであるタービン翼の製造方法。 10. The method for manufacturing a turbine blade according to claim 9, wherein the cobalt-based alloy is stellite or trivalloy.
- 請求項６から１０のいずれか一項に記載のタービン翼の製造方法において、前記シュラウドの母材はニッケル基合金であるタービン翼の製造方法。 The method for manufacturing a turbine blade according to any one of claims 6 to 10, wherein a base material of the shroud is a nickel-based alloy.
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| JP3808655B2 (en) * | 1999-02-24 | 2006-08-16 | 株式会社日立製作所 | Turbine rotor and turbine |
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| WO2017094292A1 (en) * | 2015-12-01 | 2017-06-08 | 株式会社Ihi | Sliding component provided with wear-resistant coating and method for forming wear-resistant coating |
| CN107849700A (en) * | 2015-12-01 | 2018-03-27 | 株式会社Ihi | Possess the slide unit of abrasion performance envelope and the forming method of abrasion performance envelope |
| JPWO2017094292A1 (en) * | 2015-12-01 | 2018-08-30 | 株式会社Ihi | Sliding part with wear-resistant coating and method for forming wear-resistant coating |
| US10894387B2 (en) | 2015-12-01 | 2021-01-19 | Ihi Corporation | Sliding part with wear resistant coating and method of forming wear resistant coating |
| CN107849700B (en) * | 2015-12-01 | 2021-05-11 | 株式会社Ihi | Sliding member having abrasion-resistant coating and method for forming abrasion-resistant coating |
| CN109070258A (en) * | 2016-05-26 | 2018-12-21 | 赛峰飞机发动机公司 | Gas turbine exhaust shell and its manufacturing method |
| CN109070258B (en) * | 2016-05-26 | 2021-01-15 | 赛峰飞机发动机公司 | Turbine exhaust casing and method of manufacturing the same |
| WO2022107734A1 (en) * | 2020-11-20 | 2022-05-27 | 川崎重工業株式会社 | Gas turbine engine rotation unit constituent member and method for producing same |
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| JPWO2015068227A1 (en) | 2017-03-09 |
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