WO2015068227A1 - Aube de turbine et son procédé de fabrication - Google Patents

Aube de turbine et son procédé de fabrication Download PDF

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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
Authority
WO
WIPO (PCT)
Prior art keywords
turbine blade
shroud
manufacturing
metal powder
contact portion
Prior art date
Application number
PCT/JP2013/080028
Other languages
English (en)
Japanese (ja)
Inventor
田中良造
玉井亮嗣
武藤吉彦
岩崎勇人
壁義郎
今村嘉秀
辻敏郎
Original Assignee
川崎重工業株式会社
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 川崎重工業株式会社 filed Critical 川崎重工業株式会社
Priority to PCT/JP2013/080028 priority Critical patent/WO2015068227A1/fr
Priority to JP2015546194A priority patent/JPWO2015068227A1/ja
Publication of WO2015068227A1 publication Critical patent/WO2015068227A1/fr

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Classifications

    • 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
    • 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
    • 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
    • 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

La présente invention concerne une aube de turbine et son procédé de fabrication, dont la durabilité d'une section épaisse est améliorée au niveau d'une partie de contact du carénage. Une pluralité d'aubes de turbine (1) sont disposées alignées dans la direction circonférentielle et des carénages (5) d'extrémité d'aube font contact entre les aubes de turbine (1) adjacentes. Au niveau d'une section de contact (5a) du carénage, se trouve une section épaisse (7) résistante à l'abrasion et constituée du produit de la fusion d'une poudre métallique (6) avec un faisceau d'énergie à haute densité. La poudre métallique (6) est, par exemple, de la stellite ou du triballoy, qui sont des alliages à base de cobalt.
PCT/JP2013/080028 2013-11-06 2013-11-06 Aube de turbine et son procédé de fabrication WO2015068227A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/JP2013/080028 WO2015068227A1 (fr) 2013-11-06 2013-11-06 Aube de turbine et son procédé de fabrication
JP2015546194A JPWO2015068227A1 (ja) 2013-11-06 2013-11-06 タービン翼およびその製造方法

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Application Number Priority Date Filing Date Title
PCT/JP2013/080028 WO2015068227A1 (fr) 2013-11-06 2013-11-06 Aube de turbine et son procédé de fabrication

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017094292A1 (fr) * 2015-12-01 2017-06-08 株式会社Ihi Composant coulissant pourvu d'un revêtement résistant à l'usure et procédé de formation d'un revêtement résistant à l'usure
CN109070258A (zh) * 2016-05-26 2018-12-21 赛峰飞机发动机公司 涡轮机排气壳体及其制造方法
WO2022107734A1 (fr) * 2020-11-20 2022-05-27 川崎重工業株式会社 Élément constitutif d'unité de rotation de turbine à gaz et son procédé de fabrication

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7483592B2 (ja) * 2020-11-09 2024-05-15 住友重機械工業株式会社 歯車装置及び歯車

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Publication number Priority date Publication date Assignee Title
JPH11336502A (ja) * 1998-05-27 1999-12-07 Mitsubishi Heavy Ind Ltd 蒸気タービン動翼及びこの動翼を有する蒸気タービン
JP2006016671A (ja) * 2004-07-02 2006-01-19 Hitachi Ltd Ｎｉ基合金部材とその製造法及びタービンエンジン部品並びに溶接材料とその製造法
JP2008093725A (ja) * 2006-10-13 2008-04-24 Toshiba Corp 浸食防止方法と浸食防止部を備えた部材
JP2008538399A (ja) * 2005-04-21 2008-10-23 シーメンス アクチエンゲゼルシヤフト カバープレートとこのカバープレートに被着された保護層とを備えたタービン翼
JP2012232336A (ja) * 2011-05-09 2012-11-29 Daido Steel Co Ltd 高硬度肉盛合金粉末

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JP3808655B2 (ja) * 1999-02-24 2006-08-16 株式会社日立製作所 タービンロータ及びタービン

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH11336502A (ja) * 1998-05-27 1999-12-07 Mitsubishi Heavy Ind Ltd 蒸気タービン動翼及びこの動翼を有する蒸気タービン
JP2006016671A (ja) * 2004-07-02 2006-01-19 Hitachi Ltd Ｎｉ基合金部材とその製造法及びタービンエンジン部品並びに溶接材料とその製造法
JP2008538399A (ja) * 2005-04-21 2008-10-23 シーメンス アクチエンゲゼルシヤフト カバープレートとこのカバープレートに被着された保護層とを備えたタービン翼
JP2008093725A (ja) * 2006-10-13 2008-04-24 Toshiba Corp 浸食防止方法と浸食防止部を備えた部材
JP2012232336A (ja) * 2011-05-09 2012-11-29 Daido Steel Co Ltd 高硬度肉盛合金粉末

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017094292A1 (fr) * 2015-12-01 2017-06-08 株式会社Ihi Composant coulissant pourvu d'un revêtement résistant à l'usure et procédé de formation d'un revêtement résistant à l'usure
CN107849700A (zh) * 2015-12-01 2018-03-27 株式会社Ihi 具备耐磨耗被膜的滑动部件以及耐磨耗被膜的形成方法
JPWO2017094292A1 (ja) * 2015-12-01 2018-08-30 株式会社Ihi 耐摩耗被膜を備えた摺動部品及び耐摩耗被膜の形成方法
US10894387B2 (en) 2015-12-01 2021-01-19 Ihi Corporation Sliding part with wear resistant coating and method of forming wear resistant coating
CN107849700B (zh) * 2015-12-01 2021-05-11 株式会社Ihi 具备耐磨耗被膜的滑动部件以及耐磨耗被膜的形成方法
CN109070258A (zh) * 2016-05-26 2018-12-21 赛峰飞机发动机公司 涡轮机排气壳体及其制造方法
CN109070258B (zh) * 2016-05-26 2021-01-15 赛峰飞机发动机公司 涡轮机排气壳体及其制造方法
WO2022107734A1 (fr) * 2020-11-20 2022-05-27 川崎重工業株式会社 Élément constitutif d'unité de rotation de turbine à gaz et son procédé de fabrication

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