WO2009012747A2 - Procédé de réparation - Google Patents

Procédé de réparation Download PDF

Info

Publication number
WO2009012747A2
WO2009012747A2 PCT/DE2008/001121 DE2008001121W WO2009012747A2 WO 2009012747 A2 WO2009012747 A2 WO 2009012747A2 DE 2008001121 W DE2008001121 W DE 2008001121W WO 2009012747 A2 WO2009012747 A2 WO 2009012747A2
Authority
WO
WIPO (PCT)
Prior art keywords
blade
repaired
repair method
gas turbine
welding
Prior art date
Application number
PCT/DE2008/001121
Other languages
German (de)
English (en)
Other versions
WO2009012747A3 (fr
Inventor
Armin Eberlein
Klaus-Uwe Heins
Karl-Hermann Richter
Original Assignee
Mtu Aero Engines Gmbh
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 Mtu Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Publication of WO2009012747A2 publication Critical patent/WO2009012747A2/fr
Publication of WO2009012747A3 publication Critical patent/WO2009012747A3/fr

Links

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
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/34—Laser welding for purposes other than joining
    • B23K26/342—Build-up welding
    • 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
    • F01D5/005—Repairing methods or devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines

Definitions

  • the invention relates to a repair method for turbomachinery blades, in particular for gas turbine blades.
  • Turbomachinery blades such as gas turbine blades, are subject to wear during operation.
  • the wear may necessitate repairing the turbomachinery blades after damage by removing damaged portions of the turbomachinery blades and renewing them after removing the damaged portions.
  • stator-side vanes are subject to such wear, which may require a repair of the same.
  • DE 3909733 A1 discloses a method for repairing, for example, integrally bladed gas turbine rotors, in which a damaged section of the gas turbine blade to be repaired is removed and renewed after removal of the same by welding a replacement part.
  • a damaged section of the gas turbine blade to be repaired is removed and renewed after removal of the same by welding a replacement part.
  • inductive pressure welding is used.
  • Such a method is unsuitable for repairing turbomachinery blades in the area of blade edges.
  • the present invention is based on the problem of providing a novel repair method for turbomachinery blades, in particular for gas turbine blades. This problem is solved by a repair method according to claim 1.
  • the repair method for turbomachinery blades comprises at least the following steps: a) providing a turbomachine blade to be repaired, in particular a gas turbine blade to be repaired; b) removing a damaged portion of the turbomachine blade to be repaired in the region of a blade edge, in particular in the region of a flow inlet edge or a flow outlet edge of the turbomachinery blade to be repaired; c) renewal of the removed portion by means of build-up welding, preferably laser powder build-up welding.
  • the invention proposes for the first time a method for repairing turbomachinery blades, with which turbomachinery blades can be repaired cost-effectively in the area of their blade edges while ensuring a short repair time.
  • a damaged section thereof is cut out of a turbomachine blade damaged in the region of a blade edge, the cut-out section being renewed by build-up welding, preferably by laser powder build-up welding.
  • FIG. 1 shows a schematic representation of a turbomachine blade to be repaired for clarification of the repair method according to the invention.
  • the present invention relates to a repair method for turbomachinery blades, in particular for gas turbine blades, designed as an aircraft engine gas turbine.
  • both stator-side guide vanes and rotor-side rotor blades can be repaired.
  • FIG. 1 shows a schematic representation of a turbomachine blade 10 which comprises an airfoil 11 and a blade root 12.
  • the airfoil 11 comprises two flow edges 13, 14, namely a so-called flow inlet edge 13 and a flow outlet edge 14.
  • the turbomachine blade 10 has damage 15 in the region of its flow inlet edge 13. These are z. B. caused by hail or by bird strike damage to the flow inlet edge 13.
  • the damage 15 is positioned in a middle or lower region of the flow inlet edge 13.
  • a blade tip 17 of the turbomachine blade 10 is therefore undamaged.
  • the turbomachine blade 10 is repaired in such a way that after the turbomachine blade 10 to be repaired has been removed, the damaged portion 15 is removed from the turbomachine blade 10 to be repaired in the region of the flow inlet edge 13.
  • the damaged portion 15 is removed by milling, wherein Fig. 1 shows in dashed lines a contour 16, which forms after removal of the damaged portion 16 in the region of the flow inlet edge 13.
  • the contour 16 does not extend into the region of the blade tip 17.
  • the removed portion is renewed by means of build-up welding, preferably laser powder build-up welding.
  • the removed section is renewed by build-up welding, preferably by laser powder build-up welding, so that an oversize is formed, the original contour of the turbomachine blade 10 subsequently being provided by milling in the region of the flow inlet edge 13.
  • a local heat treatment is carried out exclusively in the area of the renewed section, namely a local, inductive stress relief annealing.
  • the method according to the invention is particularly suitable for repairing stator-side guide vanes of a gas turbine, in particular stator-side guide vanes of a low-pressure compressor of a gas turbine. Both individual vanes and vanes of an integrally bladed vane ring can be repaired. With the aid of the method according to the invention, it is also possible to repair rotor-side moving blades, in particular moving blades of an integrally bladed gas turbine rotor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Laser Beam Processing (AREA)

Abstract

L'invention concerne un procédé de réparation pour ailettes de turbomachine, en particulier pour ailettes de turbine à gaz, qui comprend les étapes suivantes: (a) prendre une ailette de turbomachine à réparer, en particulier une ailette de turbine à gaz qu'il faut réparer; (b) éliminer une section endommagée de l'ailette de turbomachine à réparer, dans la région d'une arête d'ailette, en particulier dans la région d'une arête d'entrée d'écoulement ou d'une arête de sortie d'écoulement de l'ailette de turbomachine à réparer; (c) remplacement de la section ainsi éliminée par soudage avec apport, de préférence par soudage laser avec apport de poudre.
PCT/DE2008/001121 2007-07-23 2008-07-05 Procédé de réparation WO2009012747A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007034242A DE102007034242A1 (de) 2007-07-23 2007-07-23 Reparaturverfahren
DE102007034242.1 2007-07-23

Publications (2)

Publication Number Publication Date
WO2009012747A2 true WO2009012747A2 (fr) 2009-01-29
WO2009012747A3 WO2009012747A3 (fr) 2009-03-26

Family

ID=40279117

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2008/001121 WO2009012747A2 (fr) 2007-07-23 2008-07-05 Procédé de réparation

Country Status (2)

Country Link
DE (1) DE102007034242A1 (fr)
WO (1) WO2009012747A2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9574447B2 (en) 2013-09-11 2017-02-21 General Electric Company Modification process and modified article
CN108038266A (zh) * 2017-11-17 2018-05-15 西安铂力特增材技术股份有限公司 一种选择性激光修复过程的数值模拟方法
EP3441181A1 (fr) * 2017-08-09 2019-02-13 General Electric Company Procédés de traitement de composants formés à partir de matériau équiaxe ou d'une structure à solidification directionnelle et composants traités

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009016260A1 (de) * 2009-04-03 2010-10-07 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Verfahren beim Schweißen und Bauteil
DE102021114068A1 (de) 2021-05-31 2022-12-01 MTU Aero Engines AG Schaufelreparaturverfahren für abschnittsweise hohl ausgeführte Fanschaufeln

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3909733A1 (de) * 1988-03-28 1989-10-12 Gen Electric Verfahren und vorrichtung zum verbinden von zwei gegenstaenden
EP1721697A1 (fr) * 2005-05-06 2006-11-15 United Technologies Corporation Procédé pour réparer superalliage et inserts
EP1734136A2 (fr) * 2005-06-15 2006-12-20 Rolls-Royce plc Procédé et dispositif pour traitement d'un matériau
US20070111119A1 (en) * 2005-11-15 2007-05-17 Honeywell International, Inc. Method for repairing gas turbine engine compressor components

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3909733A1 (de) * 1988-03-28 1989-10-12 Gen Electric Verfahren und vorrichtung zum verbinden von zwei gegenstaenden
EP1721697A1 (fr) * 2005-05-06 2006-11-15 United Technologies Corporation Procédé pour réparer superalliage et inserts
EP1734136A2 (fr) * 2005-06-15 2006-12-20 Rolls-Royce plc Procédé et dispositif pour traitement d'un matériau
US20070111119A1 (en) * 2005-11-15 2007-05-17 Honeywell International, Inc. Method for repairing gas turbine engine compressor components

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9574447B2 (en) 2013-09-11 2017-02-21 General Electric Company Modification process and modified article
EP3441181A1 (fr) * 2017-08-09 2019-02-13 General Electric Company Procédés de traitement de composants formés à partir de matériau équiaxe ou d'une structure à solidification directionnelle et composants traités
CN109385606A (zh) * 2017-08-09 2019-02-26 通用电气公司 用于处理由等轴材料或定向凝固结构形成的部件的方法以及经处理部件
CN108038266A (zh) * 2017-11-17 2018-05-15 西安铂力特增材技术股份有限公司 一种选择性激光修复过程的数值模拟方法

Also Published As

Publication number Publication date
DE102007034242A1 (de) 2009-04-02
WO2009012747A3 (fr) 2009-03-26

Similar Documents

Publication Publication Date Title
DE10337866B4 (de) Verfahren zur Herstellung von Bauteilen für Gasturbinen
DE102005006414A1 (de) Verfahren zum Bearbeiten eines integral beschaufelten Rotors
EP2352615B1 (fr) Procédé de production ou de réparation de disques aubagés monoblocs
DE60036351T2 (de) Turbinenleitschaufelträger und Reparaturverfahren dafür
EP1678410A2 (fr) Procede de liaison d'aubes a des emplantures ou a des disques de rotor lors de la fabrication et / ou de la reparation d'aubes de turbines a gaz ou de rotors de turbines a gaz a aubes constituees d'un seul tenant avec le rotor
EP3999716B1 (fr) Aube de rotor pour une turbomachine, module de turbine associé et utilisation des mêmes
DE102005030848A1 (de) Verfahren zum Herstellen einer Schaufelspitzenpanzerung
EP1985803A1 (fr) Procédé pour la fabrication des aubes de turbine avec revêtement
DE102008002944A1 (de) Laufschaufel
DE102008055574A1 (de) Verfahren zur Reparatur eines Turbinenleitapparatsegmentes
WO2009012747A2 (fr) Procédé de réparation
WO2010034286A1 (fr) Dispositif et procédé pour le contrôle de la durée de vie
EP1805344B1 (fr) Procede de fabrication d'une piece pourvue d'un revetement de protection contre l'usure
WO2008131724A1 (fr) Semi-produit permettant de réparer une aube pour une turbine à gaz et procédé de réparation d'une aube pour une turbine à gaz
WO2009006871A2 (fr) Aube pour turbomachine
DE102007057930A1 (de) Verfahren zur Reparatur eines Dichtsegments einer Gasturbine
EP3176560B1 (fr) Procede de test une aube de turbine
EP2818641A1 (fr) Aube de turbine avec arête de plate-forme étagée et inclinée
DE102015219513A1 (de) Reparaturverfahren für Dichtsegmente
DE102006051813A1 (de) Schaufel für einen Verdichter oder eine Turbine eines Flugtriebwerks, Flugtriebwerk mit einer solchen Schaufel sowie Verfahren zum Beschichten einer Schaufel eines Flugtriebwerks
DE102004009755A1 (de) Gasturbinenschaufel
WO2019192635A1 (fr) Procédé de fabrication d'une aube d'une turbomachine
EP1914382B1 (fr) Procédé de réparation d'une aube de turbine
DE102008055575A1 (de) Verfahren zur Reparatur eines gekühlten Turbinenleitapparatsegmentes
DE102019118072A1 (de) Rotor und Verfahren zum Herstellen eines Rotors

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 08784307

Country of ref document: EP

Kind code of ref document: A2

122 Ep: pct application non-entry in european phase

Ref document number: 08784307

Country of ref document: EP

Kind code of ref document: A2