CA2422842A1 - Establishing a throat area of a gas turbine nozzle, and a technique for modifying the nozzle vanes - Google Patents
Establishing a throat area of a gas turbine nozzle, and a technique for modifying the nozzle vanes Download PDFInfo
- Publication number
- CA2422842A1 CA2422842A1 CA002422842A CA2422842A CA2422842A1 CA 2422842 A1 CA2422842 A1 CA 2422842A1 CA 002422842 A CA002422842 A CA 002422842A CA 2422842 A CA2422842 A CA 2422842A CA 2422842 A1 CA2422842 A1 CA 2422842A1
- Authority
- CA
- Canada
- Prior art keywords
- percent
- gas turbine
- turbine nozzle
- nickel
- trailing edge
- 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.)
- Granted
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
-
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- 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
- Y10T29/4932—Turbomachine making
- Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
-
- 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
- Y10T29/49764—Method of mechanical manufacture with testing or indicating
- Y10T29/49771—Quantitative measuring or gauging
-
- 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
- Y10T29/49764—Method of mechanical manufacture with testing or indicating
- Y10T29/49778—Method of mechanical manufacture with testing or indicating with aligning, guiding, or instruction
Abstract
A final throat area of a gas turbine nozzle circumferential structure is established by providing at least two gas turbine nozzle vanes (42), and determining a pairwise initial throat area between each pair of gas turbine nozzle vanes (42). For each pair of gas turbine nozzle vanes (42) whose pairwise initial throat area is not within the final pairwise throat area target range, a trailing edge (50) of at least one of the gas turbine nozzle vanes (42) is extended responsive to the step of determining the initial pairwise throat area, so that a final pairwise throat area is within a final pairwise throat area target range. A nozzle plurality of pairs of gas turbine nozzle vanes (42) that together comprise the gas turbine nozzle circumferential structure may be selected so that a sum of their final pairwise throat areas is within a final total throat area target range. The trailing edge (50) may be extended for this or other purposes by affixing an extension wire (100) to the trailing edge (50) extending lengthwise along the trailing edge (50), applying a braze material (104) to the extension wire (100) and the trailing edge (50), and heating the braze material (104) to a brazing temperature to melt at least a portion of the braze material (104) and, upon cooling, to bond the extension wire (100) and the braze material (104) to the trailing edge (50).
Claims (14)
1. A method for extending a trailing edge (50) of a gas turbine nozzle vane (42), comprising the steps of providing a gas turbine nozzle vane (42) having a rounded trailing edge (50) extending lengthwise between a root (52) and a tip (54) of the gas turbine nozzle vane (42);
affixing an extension wire (100) to the trailing edge (50) extending lengthwise along the trailing edge (50);
applying a braze material (104) to the extension wire (100) and the trailing edge (50); and heating the braze material (104) to a brazing temperature to melt at least a portion of the braze material (104) and, upon cooling, to bond the extension wire 1 (100) and the braze material (104) to the trailing edge (50).
affixing an extension wire (100) to the trailing edge (50) extending lengthwise along the trailing edge (50);
applying a braze material (104) to the extension wire (100) and the trailing edge (50); and heating the braze material (104) to a brazing temperature to melt at least a portion of the braze material (104) and, upon cooling, to bond the extension wire 1 (100) and the braze material (104) to the trailing edge (50).
2. The method of claim 1, wherein the gas turbine nozzle vane (42) is made of a nozzle-vane nickel-base superalloy, and the extension wire (100) is made of an extension-wire nickel-base superalloy.
3. The method of claim 2, wherein the extension-wire nickel-base superalloy has a nominal composition in weight percent of about 12.0 percent cobalt, about 6.8 percent chromium, about 1.5 percent molybdenum, about 4.9 percent tungsten, about 2.8 percent rhenium, about 6.35 percent tantalum, about 6.15 percent aluminum, about 1.5 percent hafnium, about 0.12 percent carbon, about 0.015 percent boron, balance nickel and minor elements.
4. The method of claim 1, wherein the step of applying the braze material (104) includes the step of:
applying a first layer (106) of a high-melt filler alloy into a gap region between the extension wire (100) and the trailing edge (50), and thereafter applying a second layer (110) of a braze composition overlying the first layer (106).
applying a first layer (106) of a high-melt filler alloy into a gap region between the extension wire (100) and the trailing edge (50), and thereafter applying a second layer (110) of a braze composition overlying the first layer (106).
5. The method of claim 4, wherein the first layer (106) is a first-layer nickel-base superalloy having a first-layer-nickel-base-superalloy melting point greater than the brazing temperature.
6. The method of claim 5, wherein the first-layer nickel-base superalloy is selected from the group consisting of:
a first nickel-base superalloy having a nominal composition, in weight percent, of about 7.5 percent cobalt, about 9.75 percent chromium, about 1.5 percent molybdenum, about 6.0 percent tungsten, about 4.8 percent tantalum, about 4.2 percent aluminum, about 3.45 percent titanium, about 0.15 percent hafnium, about 0.05 percent carbon, about 0.004 percent boron, about 0.5 percent niobium, balance nickel and minor elements, and a second nickel-base superalloy, having a nominal composition in weight percent of about 12.0 percent cobalt, about 6.8 percent chromium, about 1.5 percent molybdenum, about 4.9 percent tungsten, about 2.8 percent rhenium, about 6.35 percent tantalum, about 6.15 percent aluminum, about 1.5 percent hafnium, about 0.12 percent carbon, about 0.015 percent boron, balance nickel and minor elements.
a first nickel-base superalloy having a nominal composition, in weight percent, of about 7.5 percent cobalt, about 9.75 percent chromium, about 1.5 percent molybdenum, about 6.0 percent tungsten, about 4.8 percent tantalum, about 4.2 percent aluminum, about 3.45 percent titanium, about 0.15 percent hafnium, about 0.05 percent carbon, about 0.004 percent boron, about 0.5 percent niobium, balance nickel and minor elements, and a second nickel-base superalloy, having a nominal composition in weight percent of about 12.0 percent cobalt, about 6.8 percent chromium, about 1.5 percent molybdenum, about 4.9 percent tungsten, about 2.8 percent rhenium, about 6.35 percent tantalum, about 6.15 percent aluminum, about 1.5 percent hafnium, about 0.12 percent carbon, about 0.015 percent boron, balance nickel and minor elements.
7. The method of claim 4, wherein the second layer (110) is a second-layer nickel-base superalloy having a second-layer-nickel-base-superalloy melting point less than the brazing temperature.
8. The method of claim 7, wherein the second-layer nickel-base superalloy is a mixture of a first component having a first-component melting point greater than the brazing temperature and a second component having a second-component melting point less than the brazing temperature.
9. The method of claim 7, wherein the second-layer nickel-base superalloy is a mixture of:
a first nickel-base superalloy, having a nominal composition in weight percent of about 12.0 percent cobalt, about 6.8 percent chromium, about 1.5 percent molybdenum, about 4.9 percent tungsten, about 2.8 percent rhenium, about 6.35 percent tantalum, about 6.15 percent aluminum, about 1.5 percent hafnium, about 0.12 percent carbon, about 0.015 percent boron, balance nickel and minor elements, and a second nickel-base superalloy modified by the addition of silicon and boron and having a nominal composition, in weight percent, of about 0.16 percent carbon, about 4.5 percent silicon, about 14.0 percent chromium, about 9.5 percent cobalt, about 4.9 percent titanium, about 4.0 percent molybdenum, about 4.0 percent tungsten, about 3.0 percent aluminum, about 0.65 percent boron, about 0.03 percent zirconium, balance nickel and minor elements.
a first nickel-base superalloy, having a nominal composition in weight percent of about 12.0 percent cobalt, about 6.8 percent chromium, about 1.5 percent molybdenum, about 4.9 percent tungsten, about 2.8 percent rhenium, about 6.35 percent tantalum, about 6.15 percent aluminum, about 1.5 percent hafnium, about 0.12 percent carbon, about 0.015 percent boron, balance nickel and minor elements, and a second nickel-base superalloy modified by the addition of silicon and boron and having a nominal composition, in weight percent, of about 0.16 percent carbon, about 4.5 percent silicon, about 14.0 percent chromium, about 9.5 percent cobalt, about 4.9 percent titanium, about 4.0 percent molybdenum, about 4.0 percent tungsten, about 3.0 percent aluminum, about 0.65 percent boron, about 0.03 percent zirconium, balance nickel and minor elements.
10. The method of claim 1, wherein the brazing temperature is from about 2190°F to about 2240°F.
11. A method for establishing a final throat area of a gas turbine nozzle circumferential structure, comprising the steps of:
providing a final pairwise throat area target range;
providing at least two gas turbine nozzle vanes (42); thereafter determining a pairwise initial throat area between each pair of gas turbine nozzle vanes (42); and thereafter, for each pair of gas turbine nozzle vanes (42) whose pairwise initial throat area is not within the final pairwise throat area target range, of extending a trailing edge (50) of at least one of the gas turbine nozzle vanes (42) responsive to the step of determining the initial pairwise throat area, so that the final pairwise throat area is within the final pairwise throat area target range.
providing a final pairwise throat area target range;
providing at least two gas turbine nozzle vanes (42); thereafter determining a pairwise initial throat area between each pair of gas turbine nozzle vanes (42); and thereafter, for each pair of gas turbine nozzle vanes (42) whose pairwise initial throat area is not within the final pairwise throat area target range, of extending a trailing edge (50) of at least one of the gas turbine nozzle vanes (42) responsive to the step of determining the initial pairwise throat area, so that the final pairwise throat area is within the final pairwise throat area target range.
12. The method of claim 11, wherein the step of providing includes the step of:
providing a nozzle plurality of pairs of gas turbine nozzle vanes (42) together comprising the gas turbine nozzle circumferential structure.
providing a nozzle plurality of pairs of gas turbine nozzle vanes (42) together comprising the gas turbine nozzle circumferential structure.
13. The method of claim 11, including an additional step, of:
providing a final total throat area target range, and selecting a nozzle plurality of pairs of gas turbine nozzle vanes (42) that together comprise the gas turbine nozzle circumferential structure, wherein a sum of their final pairwise throat areas is within the final total throat area target range.
providing a final total throat area target range, and selecting a nozzle plurality of pairs of gas turbine nozzle vanes (42) that together comprise the gas turbine nozzle circumferential structure, wherein a sum of their final pairwise throat areas is within the final total throat area target range.
14. The method of claim 11, wherein the step of extending includes the steps of:
providing one of the gas turbine nozzle vanes (42) having a rounded trailing edge (50) extending lengthwise between a root (52) and a tip (54) of the gas turbine nozzle vane (42), affixing an extension wire (100) to the trailing edge (50) extending lengthwise along the trailing edge (50), applying a braze material (104) overlying the extension wire (100) and the trailing edge (50), and brazing the braze material (104) to the extension wire (100) and to the trailing edge (50).
providing one of the gas turbine nozzle vanes (42) having a rounded trailing edge (50) extending lengthwise between a root (52) and a tip (54) of the gas turbine nozzle vane (42), affixing an extension wire (100) to the trailing edge (50) extending lengthwise along the trailing edge (50), applying a braze material (104) overlying the extension wire (100) and the trailing edge (50), and brazing the braze material (104) to the extension wire (100) and to the trailing edge (50).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/104,757 US6789315B2 (en) | 2002-03-21 | 2002-03-21 | Establishing a throat area of a gas turbine nozzle, and a technique for modifying the nozzle vanes |
| US10/104,757 | 2002-03-21 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2422842A1 true CA2422842A1 (en) | 2003-09-21 |
| CA2422842C CA2422842C (en) | 2010-05-04 |
Family
ID=27804324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2422842A Expired - Fee Related CA2422842C (en) | 2002-03-21 | 2003-03-20 | Establishing a throat area of a gas turbine nozzle, and a technique for modifying the nozzle vanes |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US6789315B2 (en) |
| EP (1) | EP1348833B1 (en) |
| JP (1) | JP4169616B2 (en) |
| BR (1) | BR0300685B1 (en) |
| CA (1) | CA2422842C (en) |
| DE (1) | DE60311027T2 (en) |
| SG (1) | SG106134A1 (en) |
Families Citing this family (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7279229B2 (en) * | 2005-03-24 | 2007-10-09 | General Electric Company | Nickel-base braze material and method of filling holes therewith |
| US20070050172A1 (en) * | 2005-09-01 | 2007-03-01 | General Electric Company | Method and apparatus for measuring throat areas of gas turbine engine nozzle assemblies |
| US8342386B2 (en) * | 2006-12-15 | 2013-01-01 | General Electric Company | Braze materials and processes therefor |
| US8070454B1 (en) | 2007-12-12 | 2011-12-06 | Florida Turbine Technologies, Inc. | Turbine airfoil with trailing edge |
| US20100034692A1 (en) * | 2008-08-06 | 2010-02-11 | General Electric Company | Nickel-base superalloy, unidirectional-solidification process therefor, and castings formed therefrom |
| CH700774A1 (en) * | 2009-03-31 | 2010-10-15 | Alstom Technology Ltd | Doppellotelement, process for its preparation and uses thereof. |
| JP5573204B2 (en) * | 2010-02-01 | 2014-08-20 | ソニー株式会社 | Transceiver element |
| US10287987B2 (en) * | 2010-07-19 | 2019-05-14 | United Technologies Corporation | Noise reducing vane |
| US10072519B2 (en) * | 2013-04-24 | 2018-09-11 | Hamilton Sundstrand Corporation | Turbine nozzle for air cycle machine |
| US20140321979A1 (en) * | 2013-04-24 | 2014-10-30 | Hamilton Sundstrand Corporation | Turbine nozzle piece parts with hvoc coatings |
| US10072502B2 (en) * | 2013-04-24 | 2018-09-11 | Hamilton Sundstrand Corporation | Turbine nozzle and shroud for air cycle machine |
| US10087760B2 (en) * | 2013-04-24 | 2018-10-02 | Hamilton Sundstrand Corporation | Turbine nozzle and shroud for air cycle machine |
| US10006299B2 (en) * | 2013-04-24 | 2018-06-26 | Hamilton Sundstrand Corporation | Turbine nozzle for air cycle machine |
| US10072512B2 (en) * | 2013-04-24 | 2018-09-11 | Hamilton Sundstrand Corporation | Turbine nozzle and shroud |
| US20150041590A1 (en) * | 2013-08-09 | 2015-02-12 | General Electric Company | Airfoil with a trailing edge supplement structure |
| SG10201505961QA (en) * | 2014-08-11 | 2016-03-30 | United Technologies Corp | Die-castable nickel based superalloy composition |
| US10214804B2 (en) * | 2014-12-29 | 2019-02-26 | Hamilton Sundstrand Corporation | First stage turbine nozzle with erosion coating surface finish |
| US10196149B2 (en) * | 2014-12-29 | 2019-02-05 | Hamilton Sundstrand Corporation | Second stage turbine nozzle with erosion coating surface finish |
| GB201514724D0 (en) * | 2015-08-19 | 2015-09-30 | Rolls Royce Plc | Methods, apparatus, computer programs, and non-transitory computer readble storage mediums for repairing aerofoils of gas turbine engines |
| DE102016201764A1 (en) * | 2016-02-05 | 2017-08-10 | MTU Aero Engines AG | Repair method for turbine blades |
| PL428066A1 (en) * | 2018-12-06 | 2020-06-15 | General Electric Company | Systems and methods for contraction control |
| US11305363B2 (en) * | 2019-02-11 | 2022-04-19 | Rolls-Royce Corporation | Repair of through-hole damage using braze sintered preform |
| US11066942B2 (en) | 2019-05-13 | 2021-07-20 | Rolls-Royce Plc | Systems and method for determining turbine assembly flow characteristics |
| US11230927B2 (en) * | 2019-06-03 | 2022-01-25 | Raytheon Technologies Corporation | Vane airfoil shapes for embedded members |
| US11466581B1 (en) | 2021-05-18 | 2022-10-11 | General Electric Company | Turbine nozzle assembly system with nozzle sets having different throat areas |
| CN113513369B (en) * | 2021-07-26 | 2023-01-24 | 中国船舶重工集团公司第七0三研究所 | Method for adjusting throat area of turbine blade of marine gas turbine |
| US11692446B2 (en) | 2021-09-23 | 2023-07-04 | Rolls-Royce North American Technologies, Inc. | Airfoil with sintered powder components |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4028787A (en) | 1975-09-15 | 1977-06-14 | Cretella Salvatore | Refurbished turbine vanes and method of refurbishment thereof |
| US4307994A (en) | 1979-10-15 | 1981-12-29 | General Motors Corporation | Variable vane position adjuster |
| US4726101A (en) | 1986-09-25 | 1988-02-23 | United Technologies Corporation | Turbine vane nozzle reclassification |
| US4830934A (en) | 1987-06-01 | 1989-05-16 | General Electric Company | Alloy powder mixture for treating alloys |
| US5060842A (en) | 1990-04-09 | 1991-10-29 | Westinghouse Electric Corp. | Method for refurbishing nozzle block vanes of a steam turbine |
| US5193736A (en) | 1991-03-01 | 1993-03-16 | Interturbine Corporation | Method for repairing turbine vanes |
| US5142778A (en) | 1991-03-13 | 1992-09-01 | United Technologies Corporation | Gas turbine engine component repair |
| US5193738A (en) * | 1992-09-18 | 1993-03-16 | Microfab Technologies, Inc. | Methods and apparatus for soldering without using flux |
| DE69512296T2 (en) * | 1994-03-11 | 2000-04-13 | Agfa Gevaert Nv | Photographic materials containing polymer compounds |
| US5522134A (en) | 1994-06-30 | 1996-06-04 | United Technologies Corporation | Turbine vane flow area restoration method |
| US5569546A (en) | 1995-03-10 | 1996-10-29 | General Electric Company | Repaired article and material and method for making |
| GB9511269D0 (en) | 1995-06-05 | 1995-08-02 | Rolls Royce Plc | Variable angle vane arrays |
| WO1998019048A1 (en) | 1996-10-28 | 1998-05-07 | Siemens Westinghouse Power Corporation | Airfoil for a turbomachine |
| US6233822B1 (en) | 1998-12-22 | 2001-05-22 | General Electric Company | Repair of high pressure turbine shrouds |
| JP5073905B2 (en) | 2000-02-29 | 2012-11-14 | ゼネラル・エレクトリック・カンパニイ | Nickel-base superalloy and turbine parts manufactured from the superalloy |
| US6572330B2 (en) * | 2001-03-29 | 2003-06-03 | General Electric Company | Methods and apparatus for preferential placement of turbine nozzles and shrouds based on inlet conditions |
-
2002
- 2002-03-21 US US10/104,757 patent/US6789315B2/en not_active Expired - Lifetime
-
2003
- 2003-03-19 SG SG200301429A patent/SG106134A1/en unknown
- 2003-03-20 JP JP2003076721A patent/JP4169616B2/en not_active Expired - Fee Related
- 2003-03-20 CA CA2422842A patent/CA2422842C/en not_active Expired - Fee Related
- 2003-03-21 EP EP03251785A patent/EP1348833B1/en not_active Expired - Fee Related
- 2003-03-21 DE DE60311027T patent/DE60311027T2/en not_active Expired - Lifetime
- 2003-03-21 BR BRPI0300685-9A patent/BR0300685B1/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| JP2004036607A (en) | 2004-02-05 |
| DE60311027D1 (en) | 2007-02-22 |
| JP4169616B2 (en) | 2008-10-22 |
| US20030177640A1 (en) | 2003-09-25 |
| US6789315B2 (en) | 2004-09-14 |
| BR0300685A (en) | 2004-09-08 |
| DE60311027T2 (en) | 2007-08-16 |
| BR0300685B1 (en) | 2011-12-27 |
| SG106134A1 (en) | 2004-09-30 |
| CA2422842C (en) | 2010-05-04 |
| EP1348833B1 (en) | 2007-01-10 |
| EP1348833A1 (en) | 2003-10-01 |
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