EP1838493A1 - Verfahren zur reparatur von turbinenlaufschaufeln - Google Patents
Verfahren zur reparatur von turbinenlaufschaufelnInfo
- Publication number
- EP1838493A1 EP1838493A1 EP06705784A EP06705784A EP1838493A1 EP 1838493 A1 EP1838493 A1 EP 1838493A1 EP 06705784 A EP06705784 A EP 06705784A EP 06705784 A EP06705784 A EP 06705784A EP 1838493 A1 EP1838493 A1 EP 1838493A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- turbine
- section
- damaged
- turbine blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
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
- B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
-
- 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
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/233—Electron beam welding
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/234—Laser welding
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/235—TIG or MIG welding
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/238—Soldering
Definitions
- the invention relates to a method for repairing turbine blades of a gas turbine.
- a gas turbine in particular an aircraft engine, comprises, in addition to a combustion chamber, at least one compressor and at least one turbine.
- a turbine In the first stages of a turbine usually internally cooled turbine blades are used, which are designed as hollow blades. This is partly due to the fact that in the first stages of the turbine very high temperatures prevail, whereby an internal cooling of the blades is required.
- Such internally cooled blades have a complex internal geometry.
- less turbocharged turbine blades are designed as full blades.
- Turbine blades of gas turbines are subject during operation to high loads and thus wear, in particular by abrasion, cracking, oxidation, burns or even erosion and corrosion. Due to the above wear, it is necessary to repair the turbine blades after damage.
- the present invention is based on the problem of providing a novel method for repairing turbine blades.
- This problem is solved by a method of repairing turbine blades according to claim 1.
- the method comprises at least the following steps: a) providing a turbine blade to be repaired; b) removing a damaged airfoil portion from the turbine blade to form a blade stub; c) establishing a replacement section for the damaged and removed airfoil section of the turbine blade; d) connecting the replacement section with the corresponding blade stump.
- the method according to the invention for repairing turbine blades of a gas turbine is described below by way of example using the example of a turbine blade designed as a hollow blade. It should be noted at this point that the method according to the invention can also be used in turbine blade segments or integrally bladed rotors.
- the turbine blades to be repaired by the method according to the invention can be designed as hollow blades or as full blades.
- the procedure is such that a damaged blade section is removed from a provided turbine blade to be repaired to form a blade stump.
- a parting plane and thus a subsequent joining plane is approximately parallel to a rotation axis of a gas turbine rotor and thus approximately horizontal.
- the damaged blade section is preferably separated from the hollow blade in such a way that the separation plane runs as close as possible to the blade tip of the hollow blade. It is also possible to position the parting plane as far as the blade platform or a blade root.
- This replacement section has exactly the geometry of the damaged, severed airfoil section in undamaged form.
- the replacement section is produced by investment casting or by powder metallurgy manufacturing, in particular by powder metallurgical injection molding. It is possible to make the replacement section of the same material as the damaged and severed airfoil section. However, it is also possible to produce the replacement section from another material with a better wear behavior or better joining properties.
- the replacement section produced is connected to the blade stump which has formed in the region of the severed damaged blade section.
- the joining surfaces of the blade stub and the replacement section are machined by grinding.
- the joining or joining of the replacement section with the corresponding blade stump is carried out either by beam welding or by soldering.
- the replacement section is connected to the corresponding blade stump by beam welding, in particular laser beam welding or electron beam welding is used. Due to the small focus that can be realized during laser beam welding and electron beam welding, precise joining of the blade stump to the replacement section is possible so that both inner contours and outer contours are completely welded. This is important in the case of hollow blades, since no reworking is possible on the inner contours of the hollow blades after welding.
- connection of the replacement section with the blade stump can be done by soldering.
- the soldering is carried out using as little solder as possible, in particular using thin solder foils or so-called solder tapes, which are geometrically adapted to the joining surface.
- a solder foil which is geometrically preformed according to the respective joining surface is applied to the joining surface, and subsequently the replacement section is connected to the blade stump in a soldering process.
- this method enables the setting of a defined monocrystalline or directionally solidified microstructure within the joining zone, with slow cooling from the soldering temperature. Thus, a decrease in strength in the joint zone at the respective solder seams can be avoided.
- the present invention proposes a method of repairing turbine blades, which is particularly suitable for repairing turbine blades, which are usually made of superalloys and can be configured as hollow blades.
- the method according to the invention is particularly suitable for repairing turbine blades of a high-pressure turbine and a low-pressure turbine.
- the repairable damage spectrum of turbine blades is significantly expanded, since complex damage patterns can now also be repaired. It can also be repaired large damage that could not be repaired with previously used methods for crack and construction welding.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200510002609 DE102005002609A1 (de) | 2005-01-20 | 2005-01-20 | Verfahren zur Reparatur von Turbinenlaufschaufeln |
PCT/DE2006/000045 WO2006076884A1 (de) | 2005-01-20 | 2006-01-13 | Verfahren zur reparatur von turbinenlaufschaufeln |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1838493A1 true EP1838493A1 (de) | 2007-10-03 |
Family
ID=36169150
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06705784A Withdrawn EP1838493A1 (de) | 2005-01-20 | 2006-01-13 | Verfahren zur reparatur von turbinenlaufschaufeln |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP1838493A1 (de) |
DE (1) | DE102005002609A1 (de) |
WO (1) | WO2006076884A1 (de) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006049219A1 (de) | 2006-10-18 | 2008-04-30 | Mtu Aero Engines Gmbh | Hochdruckturbinen-Schaufel und Verfahren zur Reparatur von Hochdruckturbinen-Schaufeln |
DE102008025848A1 (de) * | 2008-05-29 | 2009-12-03 | Mtu Aero Engines Gmbh | Verfahren zur Reparatur von einkristallinen Hochdruckturbinenschaufeln durch Diffusionslöten |
DE102008058140A1 (de) * | 2008-11-20 | 2010-05-27 | Mtu Aero Engines Gmbh | Verfahren zur Reparatur von einkristallinen Turbinenschaufeln |
FR2949366B1 (fr) * | 2009-08-31 | 2011-11-18 | Snecma | Realisation par procede mim d'un morceau de piece pour la reparation d'une aube de distributeur de turbine |
EP2583781B1 (de) * | 2011-10-21 | 2014-06-25 | Siemens Aktiengesellschaft | Kombinierter Schweiß-Löt-Prozess zum Verbinden von zwei Komponenten |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0401187A2 (de) * | 1989-06-01 | 1990-12-05 | Abb Stal Ab | Verfahren zum Wiederaufbauen von Flügeln mit Erosionsschaden in Dampfturbinen |
US20010014403A1 (en) * | 1997-08-12 | 2001-08-16 | Lawrence Evans Brown | Method and apparatus for making components by direct laser processing |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4152488A (en) * | 1977-05-03 | 1979-05-01 | United Technologies Corporation | Gas turbine blade tip alloy and composite |
US4883216A (en) * | 1988-03-28 | 1989-11-28 | General Electric Company | Method for bonding an article projection |
DE19642980C1 (de) * | 1996-10-18 | 1998-08-13 | Mtu Muenchen Gmbh | Verfahren zur Instandsetzung verschlissener Schaufelspitzen von Verdichter- und Turbinenschaufel |
US5822852A (en) * | 1997-07-14 | 1998-10-20 | General Electric Company | Method for replacing blade tips of directionally solidified and single crystal turbine blades |
DE19831736C2 (de) * | 1998-07-15 | 2000-05-31 | Mtu Muenchen Gmbh | Verfahren zur Reparatur und Herstellung eines integral beschaufelten Rotors für eine Strömungsmaschine |
JP2000263247A (ja) * | 1999-03-10 | 2000-09-26 | Ishikawajima Harima Heavy Ind Co Ltd | 方向制御結晶合金部品の補修方法 |
US6238187B1 (en) * | 1999-10-14 | 2001-05-29 | Lsp Technologies, Inc. | Method using laser shock peening to process airfoil weld repairs pertaining to blade cut and weld techniques |
US6508000B2 (en) * | 2001-02-08 | 2003-01-21 | Siemens Westinghouse Power Corporation | Transient liquid phase bonding repair for advanced turbine blades and vanes |
US6908288B2 (en) * | 2001-10-31 | 2005-06-21 | General Electric Company | Repair of advanced gas turbine blades |
DE10319494A1 (de) * | 2003-04-30 | 2004-11-18 | Mtu Aero Engines Gmbh | Verfahren zur Reparatur und/oder Modifikation von Bauteilen einer Gasturbine |
US20050091848A1 (en) * | 2003-11-03 | 2005-05-05 | Nenov Krassimir P. | Turbine blade and a method of manufacturing and repairing a turbine blade |
US20050102835A1 (en) * | 2003-11-14 | 2005-05-19 | Trewiler Gary E. | Method for repairing gas turbine rotor blades |
-
2005
- 2005-01-20 DE DE200510002609 patent/DE102005002609A1/de not_active Withdrawn
-
2006
- 2006-01-13 WO PCT/DE2006/000045 patent/WO2006076884A1/de active Application Filing
- 2006-01-13 EP EP06705784A patent/EP1838493A1/de not_active Withdrawn
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0401187A2 (de) * | 1989-06-01 | 1990-12-05 | Abb Stal Ab | Verfahren zum Wiederaufbauen von Flügeln mit Erosionsschaden in Dampfturbinen |
US20010014403A1 (en) * | 1997-08-12 | 2001-08-16 | Lawrence Evans Brown | Method and apparatus for making components by direct laser processing |
Non-Patent Citations (1)
Title |
---|
See also references of WO2006076884A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2006076884A1 (de) | 2006-07-27 |
DE102005002609A1 (de) | 2006-08-03 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20070716 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
DAX | Request for extension of the european patent (deleted) | ||
17Q | First examination report despatched |
Effective date: 20081113 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES GMBH |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES AG |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20170801 |