WO2002090039A1 - Method of repairing a turbin blade tip - Google Patents
Method of repairing a turbin blade tip Download PDFInfo
- Publication number
- WO2002090039A1 WO2002090039A1 PCT/US2002/005250 US0205250W WO02090039A1 WO 2002090039 A1 WO2002090039 A1 WO 2002090039A1 US 0205250 W US0205250 W US 0205250W WO 02090039 A1 WO02090039 A1 WO 02090039A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- tip
- rail
- blade tip
- strengthening rib
- Prior art date
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
- 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
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49318—Repairing or disassembling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49718—Repairing
- Y10T29/49721—Repairing with disassembling
- Y10T29/4973—Replacing of defective part
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49718—Repairing
- Y10T29/49732—Repairing by attaching repair preform, e.g., remaking, restoring, or patching
- Y10T29/49734—Repairing by attaching repair preform, e.g., remaking, restoring, or patching and removing damaged material
- Y10T29/49737—Metallurgically attaching preform
Definitions
- the blade tip cap 2 generally has an airfoil shaped closure plate 3 and a tip rail 4 extending around the circumference of the turbine blade at the tip (see Figs. 1 and 2) .
- the tip rail may completely enclose the tip pocket, or may have a slot or opening, typically at the trailing edge on the concave side. In either case, it is a mandatory part of any standard blade refurbishment process to restore the overall blade length, including the rail around the tip cap pocket .
- the tip of the blades When the blades run in the engine, the tip of the blades have a very tight clearance with the engine case to prevent gasses flowing through the engine from passing in an inefficient fashion over the tops of the blades. In most engine designs, the blades actually contact a rub surface in the engine case. There is therefore some amount of physical wear on the blade tips. If the contact is extreme, it may result in fracture or breakage of portions of the tip rail. Blade damage of this type is dependent upon' the basic blade design, along with the operating conditions experienced by any individual engine.
- Turbine blades that are particularly susceptible to fracture of tip rails around the blade tip cap pocket are designed and manufactured with a very tall, thin rail around the blade tip.
- the tip rail is typically 0.250" - 0.300" high, with a wall thickness as thin as 0.015". It is common for the tip rail on these blades to fracture during engine operation. The breakage occurs on both new and previously repaired parts and regardless of the type of alloy used to restore the tip rail . Even though engines may be allowed to operate with this type of distress, there is a measurable performance loss due to lack of proper clearances at the tips of the affected blades. The performance loss translates into increased operating costs to the engine operators. There is also significant adverse cost impact when engines must be removed from service for repair of these damaged blades .
- a process for repairing a blade tip cap of a turbine blade comprising restoring the tip rail of the blade tip cap and attaching a strengthening rib across the blade tip cap connecting a concave wall to a convex wall of the tip rail .
- the strengthening rib is positioned over an internal rib below the blade tip cap of the turbine blade .
- Fig. 1 is a side view of a turbine blade showing the strengthening rib incorporated according to this invention.
- Fig. 2 is an end view of a blade tip cap according to this invention.
- This invention provides a method of repairing blade tips, involving the incorporation of a strengthening rib 5 that spans the blade tip cap connecting the concave wall 6 to the convex wall 7 of the tip rail 4 (see Figs. 1 and 2) .
- the strengthening rib 5 is positioned above a central rib 8 cast into the blade internal cavity below the blade tip cap 2 surface to provide additional strength to the tip rail 4.
- the strengthening rib is incorporated into the blade tip during the performance of a conventional blade length restoration repair to provide additional support to the tip rail.
- the strengthening rib is a cost effective solution to the tip rail breakage problem. Implementation of this repair process will save engine operators the otherwise unnecessary expenses related to engine overhauls or performance losses due to tip rail breakage.
- This repair process can be easily accomplished during the performance of a standard tip repair, utilizing existing laser welding equipment with no additional tooling.
- the new blade tip cap configuration does not adversely affect blade airflow, weight, or balance. While a specific configuration has been described, other similar configurations that achieve the same basic goal are possible. For instance, the stiffening rib could connect the concave and convex walls, but not extend all the way to the top of the blade tip. This same repair scheme can be successfully applied to any turbine blades with a substantially similar blade tip cap configuration.
- a CF6-50 second stage high pressure turbine blade was determined to be a suitable candidate for tip • length restoration.
- the blade was then processed through all of the standard repair procedures up until the tip crack welding operation.
- the primary operations prior to weld consist of internal cleaning, removal of coating at the blade tip, vacuum stress relief cycles, removal of most of the remaining tip rail, and notching to remove cracks at the blade tip. Cracks at the blade tip were then restored by manual welding at elevated temperature.
- a single pass of weld was applied across the blade tip cap joining the residual concave and convex wall of the tip rail .
- the weld pass was positioned immediately on top of the internal rib below the tip cap surface. X-ray and fluorescent penetrant inspections were performed to ensure that all cracks had been repaired.
- the residual blade tip rail was then ground perfectly flat in preparation of preheated interactive laser weld.
- a preheated interactive laser welding system welds a series of passes around the circumference of the blade tip to restore the tip rail and therefore the overall blade length.
- the weld program was modified in order to add material across the tip rail and strengthening rib surface during each weld pass .
- the result was a strengthening rib welded integrally to the blade tip cap, connecting the concave and convex walls of the tip rail (Fig. 2) .
- the blade was ground to final length and the external contour was restored. Due to the precision of the laser weld process, it was not necessary to EDM or otherwise dress the internal contour of the blade tip cap pockets. Final DT, heat treatment, and coating operations were performed.
- the blade was then subjected to destructive metallurgical analysis. The structure and integrity of the tip weld was acceptable .
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP02721107A EP1385668A4 (en) | 2001-05-07 | 2002-02-12 | Method of repairing a turbin blade tip |
MXPA03010117A MXPA03010117A (en) | 2001-05-07 | 2002-02-12 | Method of repairing a turbin blade tip. |
CA002445409A CA2445409C (en) | 2001-05-07 | 2002-02-12 | Method of repairing a turbine blade tip |
JP2002587156A JP3990985B2 (en) | 2001-05-07 | 2002-02-12 | How to repair turbine blade tips |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/850,362 | 2001-05-07 | ||
US09/850,362 US6502303B2 (en) | 2001-05-07 | 2001-05-07 | Method of repairing a turbine blade tip |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2002090039A1 true WO2002090039A1 (en) | 2002-11-14 |
Family
ID=25307921
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2002/005250 WO2002090039A1 (en) | 2001-05-07 | 2002-02-12 | Method of repairing a turbin blade tip |
Country Status (6)
Country | Link |
---|---|
US (1) | US6502303B2 (en) |
EP (1) | EP1385668A4 (en) |
JP (1) | JP3990985B2 (en) |
CA (1) | CA2445409C (en) |
MX (1) | MXPA03010117A (en) |
WO (1) | WO2002090039A1 (en) |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7001150B2 (en) * | 2003-10-16 | 2006-02-21 | Pratt & Whitney Canada Corp. | Hollow turbine blade stiffening |
US20060200963A1 (en) * | 2005-03-11 | 2006-09-14 | United Technologies Corporation | Method for repairing parts composed of superalloys |
US8512003B2 (en) * | 2006-08-21 | 2013-08-20 | General Electric Company | Tip ramp turbine blade |
US8500396B2 (en) * | 2006-08-21 | 2013-08-06 | General Electric Company | Cascade tip baffle airfoil |
US7959409B2 (en) * | 2007-03-01 | 2011-06-14 | Honeywell International Inc. | Repaired vane assemblies and methods of repairing vane assemblies |
US8091228B2 (en) * | 2007-08-21 | 2012-01-10 | United Technologies Corporation | Method repair of turbine blade tip |
US8206121B2 (en) * | 2008-03-26 | 2012-06-26 | United Technologies Corporation | Method of restoring an airfoil blade |
US20090320288A1 (en) * | 2008-06-30 | 2009-12-31 | Caterpillar Inc. | Method for repairing a turbine |
US8887390B2 (en) | 2008-08-15 | 2014-11-18 | Dresser-Rand Company | Method for correcting downstream deflection in gas turbine nozzles |
US9085053B2 (en) * | 2009-12-22 | 2015-07-21 | United Technologies Corporation | In-situ turbine blade tip repair |
US10665040B2 (en) | 2010-08-27 | 2020-05-26 | Zonar Systems, Inc. | Method and apparatus for remote vehicle diagnosis |
US10600096B2 (en) | 2010-11-30 | 2020-03-24 | Zonar Systems, Inc. | System and method for obtaining competitive pricing for vehicle services |
US20130318996A1 (en) * | 2012-06-01 | 2013-12-05 | General Electric Company | Cooling assembly for a bucket of a turbine system and method of cooling |
EP2861830B1 (en) | 2012-06-13 | 2017-09-13 | United Technologies Corporation | Tip fabrication for rotor blade or stator vane airfoil |
US9334742B2 (en) * | 2012-10-05 | 2016-05-10 | General Electric Company | Rotor blade and method for cooling the rotor blade |
WO2014143310A1 (en) | 2013-03-15 | 2014-09-18 | Rolls-Royce Corporation | Repair of gas turbine engine components |
US20150308449A1 (en) * | 2014-03-11 | 2015-10-29 | United Technologies Corporation | Gas turbine engine component with brazed cover |
US20150300180A1 (en) * | 2014-04-22 | 2015-10-22 | United Technologies Corporation | Gas turbine engine turbine blade tip with coated recess |
US20150345301A1 (en) * | 2014-05-29 | 2015-12-03 | General Electric Company | Rotor blade cooling flow |
US10107108B2 (en) | 2015-04-29 | 2018-10-23 | General Electric Company | Rotor blade having a flared tip |
SG10201700339YA (en) | 2016-02-29 | 2017-09-28 | Rolls Royce Corp | Directed energy deposition for processing gas turbine engine components |
WO2020092234A1 (en) * | 2018-10-29 | 2020-05-07 | Chromalloy Gas Turbine Llc | Method and apparatus for improving cooling of a turbine shroud |
US11339668B2 (en) | 2018-10-29 | 2022-05-24 | Chromalloy Gas Turbine Llc | Method and apparatus for improving cooling of a turbine shroud |
US11980938B2 (en) | 2020-11-24 | 2024-05-14 | Rolls-Royce Corporation | Bladed disk repair process with shield |
US11629412B2 (en) | 2020-12-16 | 2023-04-18 | Rolls-Royce Corporation | Cold spray deposited masking layer |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5822852A (en) * | 1997-07-14 | 1998-10-20 | General Electric Company | Method for replacing blade tips of directionally solidified and single crystal turbine blades |
US5913555A (en) * | 1996-10-18 | 1999-06-22 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Methods of repairing worn blade tips of compressor and turbine blades |
US6283356B1 (en) * | 1999-05-28 | 2001-09-04 | General Electric Company | Repair of a recess in an article surface |
US6332272B1 (en) * | 2000-01-07 | 2001-12-25 | Siemens Westinghouse Power Corporation | Method of repairing a turbine blade |
US6339878B1 (en) * | 2000-03-27 | 2002-01-22 | United Technologies Corporation | Method of repairing an airfoil |
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US3606580A (en) | 1969-09-10 | 1971-09-20 | Cyclops Corp | Hollow airfoil members |
US3854842A (en) | 1973-04-30 | 1974-12-17 | Gen Electric | Rotor blade having improved tip cap |
US4010531A (en) | 1975-09-02 | 1977-03-08 | General Electric Company | Tip cap apparatus and method of installation |
US4169020A (en) | 1977-12-21 | 1979-09-25 | General Electric Company | Method for making an improved gas seal |
US4214355A (en) | 1977-12-21 | 1980-07-29 | General Electric Company | Method for repairing a turbomachinery blade tip |
US4232995A (en) | 1978-11-27 | 1980-11-11 | General Electric Company | Gas seal for turbine blade tip |
US4390320A (en) | 1980-05-01 | 1983-06-28 | General Electric Company | Tip cap for a rotor blade and method of replacement |
US4411597A (en) | 1981-03-20 | 1983-10-25 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Tip cap for a rotor blade |
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US5160822A (en) * | 1991-05-14 | 1992-11-03 | General Electric Company | Method for depositing material on the tip of a gas turbine engine airfoil using linear translational welding |
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DE19542080C1 (en) | 1995-11-11 | 1997-01-30 | Mtu Muenchen Gmbh | Blade for turbo engines for the production of impellers with integral hollow blades |
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US6054672A (en) * | 1998-09-15 | 2000-04-25 | Chromalloy Gas Turbine Corporation | Laser welding superalloy articles |
US6165345A (en) * | 1999-01-14 | 2000-12-26 | Chromalloy Gas Turbine Corporation | Electrochemical stripping of turbine blades |
US6037563A (en) * | 1999-03-01 | 2000-03-14 | Chromalloy Gas Turbine Corporation | Protective gas shroud for welding |
US6107598A (en) * | 1999-08-10 | 2000-08-22 | Chromalloy Gas Turbine Corporation | Maskant for use during laser welding or drilling |
US6187450B1 (en) | 1999-10-21 | 2001-02-13 | General Electric Company | Tip cap hole brazing and oxidation resistant alloy therefor |
US6333484B1 (en) * | 2000-03-17 | 2001-12-25 | Chromalloy Gas Turbine Corporation | Welding superalloy articles |
-
2001
- 2001-05-07 US US09/850,362 patent/US6502303B2/en not_active Expired - Fee Related
-
2002
- 2002-02-12 CA CA002445409A patent/CA2445409C/en not_active Expired - Fee Related
- 2002-02-12 EP EP02721107A patent/EP1385668A4/en not_active Withdrawn
- 2002-02-12 JP JP2002587156A patent/JP3990985B2/en not_active Expired - Fee Related
- 2002-02-12 MX MXPA03010117A patent/MXPA03010117A/en active IP Right Grant
- 2002-02-12 WO PCT/US2002/005250 patent/WO2002090039A1/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5913555A (en) * | 1996-10-18 | 1999-06-22 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Methods of repairing worn blade tips of compressor and turbine blades |
US5822852A (en) * | 1997-07-14 | 1998-10-20 | General Electric Company | Method for replacing blade tips of directionally solidified and single crystal turbine blades |
US6283356B1 (en) * | 1999-05-28 | 2001-09-04 | General Electric Company | Repair of a recess in an article surface |
US6332272B1 (en) * | 2000-01-07 | 2001-12-25 | Siemens Westinghouse Power Corporation | Method of repairing a turbine blade |
US6339878B1 (en) * | 2000-03-27 | 2002-01-22 | United Technologies Corporation | Method of repairing an airfoil |
Non-Patent Citations (1)
Title |
---|
See also references of EP1385668A4 * |
Also Published As
Publication number | Publication date |
---|---|
US20020162220A1 (en) | 2002-11-07 |
MXPA03010117A (en) | 2004-03-10 |
CA2445409C (en) | 2006-08-29 |
EP1385668A4 (en) | 2007-09-12 |
CA2445409A1 (en) | 2002-11-14 |
JP3990985B2 (en) | 2007-10-17 |
JP2004530827A (en) | 2004-10-07 |
EP1385668A1 (en) | 2004-02-04 |
US6502303B2 (en) | 2003-01-07 |
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