JP2004286014A - 鋳造ノズルの組み立て式修理 - Google Patents
鋳造ノズルの組み立て式修理 Download PDFInfo
- Publication number
- JP2004286014A JP2004286014A JP2003385261A JP2003385261A JP2004286014A JP 2004286014 A JP2004286014 A JP 2004286014A JP 2003385261 A JP2003385261 A JP 2003385261A JP 2003385261 A JP2003385261 A JP 2003385261A JP 2004286014 A JP2004286014 A JP 2004286014A
- Authority
- JP
- Japan
- Prior art keywords
- inner band
- collar
- nozzle segment
- band
- replacement casting
- 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
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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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】 この方法は、内側バンドをノズルセグメントから分離しと、該内側バンドを外側バンドと少なくとも1つ羽根とを有する新規に製造された交換鋳造品に接合する。交換鋳造品は、取付けプラットホームと該取付けプラットホーム上に形成されたボスとを含む。カラーが、内側バンドに接合され、その中にスロットが形成される。次ぎに、ボスは、スロット内に挿入され、また取付けプラットホームは、内側バンド内に形成された凹部内に受入れられる。接合する際に、ボスをカラーに接合し、また取付けプラットホームを内側バンドに接合する。カラーの厚さは、軸方向にテーパが付けられ、また逃がしが、カラー内に形成されて、隣接する構成部品との間に組み立て間隙を形成する。
【選択図】 図3
Description
32 外側バンド
34 羽根
38 カラー
44 取付けプラットホーム
46 ボス
48 ダンプ孔
50 基準表面
Claims (10)
- 外側及び内側バンド間に配置された少なくとも1つ羽根を有するタービンノズルセグメントを修理する方法であって、
前記内側バンドを前記ノズルセグメントから分離する段階と、
前記内側バンド内の損傷を修理する段階と、
前記内側バンドを外側バンドと少なくとも1つの羽根とを有する新規に製造された交換鋳造品に接合する段階と、を含み、
前記内側バンドを新規に製造された交換鋳造品に接合する前記段階が、
その中に受入れスロットが形成されかつその第2の軸方向端部におけるよりもその第1の軸方向端部において大きい厚さを有するようにテーパが付けられたカラーを、前記内側バンドに接合する段階と、
前記交換鋳造品の羽根の1部分を前記受入れスロット内に挿入する段階と、
前記交換鋳造品の羽根を前記カラーと前記内側バンドとに接合する段階と、を含む、
ことを特徴とする方法。 - 前記カラーの厚さが、該カラーの軸方向前端部において最も大きいことを特徴とする、請求項1に記載の方法。
- 前記カラーの半径方向内側表面を機械加工して、円周方向に延びる円弧形の表面を形成する段階を更に含むことを特徴とする、請求項1に記載の方法。
- 前記内側バンド内にポケットを形成する段階を更に含み、前記カラーが、前記ポケットにおいて前記内側バンドに接合されることを特徴とする、請求項1に記載の方法。
- 前記カラーが、前記内側バンドに接合され、また前記交換鋳造品の羽根が、前記カラーと前記内側バンドとにろう付けにより接合されることを特徴とする、請求項1に記載の方法。
- 前記内側バンドを前記ノズルセグメントから分離する前記段階が、前記内側バンドの近くにおいて前記ノズルセグメントの羽根を切断する段階を含むことを特徴とする、請求項1に記載の方法。
- 前記交換鋳造品が、前記内側バンドと同じ材料から製作されていることを特徴とする、請求項1に記載の方法。
- 前記交換鋳造品が、前記内側バンドが製作されている材料に対して高められた材料特性を有する材料から製作されていることを特徴とする、請求項1に記載の方法。
- 前記カラーの半径方向内側表面内に逃がしを機械加工する段階を更に含むことを特徴とする、請求項1に記載の方法。
- 前記ノズルセグメントの羽根が、第1の設計を有し、また前記交換鋳造品の羽根が、改良された設計を有することを特徴とする、請求項1に記載の方法。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/295,185 US6793457B2 (en) | 2002-11-15 | 2002-11-15 | Fabricated repair of cast nozzle |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2004286014A true JP2004286014A (ja) | 2004-10-14 |
JP2004286014A5 JP2004286014A5 (ja) | 2006-12-28 |
JP4474146B2 JP4474146B2 (ja) | 2010-06-02 |
Family
ID=32176202
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2003385261A Expired - Fee Related JP4474146B2 (ja) | 2002-11-15 | 2003-11-14 | 鋳造ノズルの組み立て式修理 |
Country Status (7)
Country | Link |
---|---|
US (1) | US6793457B2 (ja) |
EP (1) | EP1419849B1 (ja) |
JP (1) | JP4474146B2 (ja) |
BR (1) | BRPI0305595B1 (ja) |
CA (1) | CA2448465C (ja) |
DE (1) | DE60321528D1 (ja) |
SG (1) | SG120960A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007182877A (ja) * | 2005-12-22 | 2007-07-19 | General Electric Co <Ge> | タービンエンジン翼組立体を修理するための方法および修理された組立体 |
JP2013002444A (ja) * | 2011-06-17 | 2013-01-07 | General Electric Co <Ge> | タービンエンジンのタービンノズルセグメントを補修する方法 |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7222422B2 (en) * | 2004-02-16 | 2007-05-29 | General Electric Company | Method for refurbishing surfaces subjected to high compression contact |
US7172389B2 (en) * | 2004-11-16 | 2007-02-06 | General Electric Company | Method for making a repaired turbine engine stationary vane assembly and repaired assembly |
US7185433B2 (en) * | 2004-12-17 | 2007-03-06 | General Electric Company | Turbine nozzle segment and method of repairing same |
US20070012370A1 (en) * | 2005-07-18 | 2007-01-18 | Honeywell International, Inc. | Facetted high temperature thruster design |
KR101412675B1 (ko) * | 2005-12-21 | 2014-07-03 | 얀센 파마슈티카 엔.브이. | 티로신 키나제 모듈레이터로서의 트리아졸로피리다진 |
US20070274854A1 (en) * | 2006-05-23 | 2007-11-29 | General Electric Company | Method of making metallic composite foam components |
US20070295785A1 (en) * | 2006-05-31 | 2007-12-27 | General Electric Company | Microwave brazing using mim preforms |
US7845549B2 (en) * | 2006-05-31 | 2010-12-07 | General Electric Company | MIM braze preforms |
US7806650B2 (en) * | 2006-08-29 | 2010-10-05 | General Electric Company | Method and apparatus for fabricating a nozzle segment for use with turbine engines |
US7837437B2 (en) * | 2007-03-07 | 2010-11-23 | General Electric Company | Turbine nozzle segment and repair method |
US8220150B2 (en) * | 2007-05-22 | 2012-07-17 | United Technologies Corporation | Split vane cluster repair method |
US7798773B2 (en) * | 2007-08-06 | 2010-09-21 | United Technologies Corporation | Airfoil replacement repair |
US8020295B2 (en) * | 2007-10-18 | 2011-09-20 | United Technologies Corp. | Methods for dimensionally restoring a fastener for a gas turbine engine |
US8296945B2 (en) * | 2007-12-29 | 2012-10-30 | General Electric Company | Method for repairing a turbine nozzle segment |
US20090274562A1 (en) * | 2008-05-02 | 2009-11-05 | United Technologies Corporation | Coated turbine-stage nozzle segments |
US8210807B2 (en) * | 2008-08-28 | 2012-07-03 | United Technologies Corporation | Gas turbine airfoil assemblies and methods of repair |
US8245399B2 (en) * | 2009-01-20 | 2012-08-21 | United Technologies Corporation | Replacement of part of engine case with dissimilar material |
US8544173B2 (en) * | 2010-08-30 | 2013-10-01 | General Electric Company | Turbine nozzle biform repair |
US8763403B2 (en) | 2010-11-19 | 2014-07-01 | United Technologies Corporation | Method for use with annular gas turbine engine component |
FR2970733B1 (fr) * | 2011-01-25 | 2015-10-16 | Snecma | Procede de controle du calage de pales dans un redresseur de turboreacteur, et pale de redresseur. |
US9097124B2 (en) | 2012-01-24 | 2015-08-04 | United Technologies Corporation | Gas turbine engine stator vane assembly with inner shroud |
US9844826B2 (en) * | 2014-07-25 | 2017-12-19 | Honeywell International Inc. | Methods for manufacturing a turbine nozzle with single crystal alloy nozzle segments |
BE1022513B1 (fr) * | 2014-11-18 | 2016-05-19 | Techspace Aero S.A. | Virole interne de compresseur de turbomachine axiale |
FR3057295B1 (fr) | 2016-10-12 | 2020-12-11 | Safran Aircraft Engines | Aube comprenant une plate-forme et une pale assemblees |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3802046A (en) | 1972-01-27 | 1974-04-09 | Chromalloy American Corp | Method of making or reconditioning a turbine-nozzle or the like assembly |
US3909157A (en) * | 1972-01-27 | 1975-09-30 | Chromalloy American Corp | Turbine nozzle-vane construction |
US4305697A (en) | 1980-03-19 | 1981-12-15 | General Electric Company | Method and replacement member for repairing a gas turbine engine vane assembly |
US4326833A (en) | 1980-03-19 | 1982-04-27 | General Electric Company | Method and replacement member for repairing a gas turbine engine blade member |
US4883216A (en) * | 1988-03-28 | 1989-11-28 | General Electric Company | Method for bonding an article projection |
US5272809A (en) | 1990-09-04 | 1993-12-28 | United Technologies Corporation | Technique for direct bonding cast and wrought materials |
US5269057A (en) | 1991-12-24 | 1993-12-14 | Freedom Forge Corporation | Method of making replacement airfoil components |
US5690469A (en) | 1996-06-06 | 1997-11-25 | United Technologies Corporation | Method and apparatus for replacing a vane assembly in a turbine engine |
US5813832A (en) | 1996-12-05 | 1998-09-29 | General Electric Company | Turbine engine vane segment |
US5758416A (en) | 1996-12-05 | 1998-06-02 | General Electric Company | Method for repairing a turbine engine vane segment |
US5797725A (en) | 1997-05-23 | 1998-08-25 | Allison Advanced Development Company | Gas turbine engine vane and method of manufacture |
US6183192B1 (en) | 1999-03-22 | 2001-02-06 | General Electric Company | Durable turbine nozzle |
US6173491B1 (en) | 1999-08-12 | 2001-01-16 | Chromalloy Gas Turbine Corporation | Method for replacing a turbine vane airfoil |
US6154959A (en) | 1999-08-16 | 2000-12-05 | Chromalloy Gas Turbine Corporation | Laser cladding a turbine engine vane platform |
US6416278B1 (en) * | 2000-11-16 | 2002-07-09 | General Electric Company | Turbine nozzle segment and method of repairing same |
US6494677B1 (en) * | 2001-01-29 | 2002-12-17 | General Electric Company | Turbine nozzle segment and method of repairing same |
-
2002
- 2002-11-15 US US10/295,185 patent/US6793457B2/en not_active Expired - Lifetime
-
2003
- 2003-11-06 CA CA2448465A patent/CA2448465C/en not_active Expired - Fee Related
- 2003-11-12 SG SG200306770A patent/SG120960A1/en unknown
- 2003-11-12 DE DE60321528T patent/DE60321528D1/de not_active Expired - Lifetime
- 2003-11-12 EP EP03257115A patent/EP1419849B1/en not_active Revoked
- 2003-11-14 JP JP2003385261A patent/JP4474146B2/ja not_active Expired - Fee Related
- 2003-11-14 BR BRPI0305595-7A patent/BRPI0305595B1/pt not_active IP Right Cessation
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2007182877A (ja) * | 2005-12-22 | 2007-07-19 | General Electric Co <Ge> | タービンエンジン翼組立体を修理するための方法および修理された組立体 |
JP2013002444A (ja) * | 2011-06-17 | 2013-01-07 | General Electric Co <Ge> | タービンエンジンのタービンノズルセグメントを補修する方法 |
Also Published As
Publication number | Publication date |
---|---|
SG120960A1 (en) | 2006-04-26 |
BRPI0305595B1 (pt) | 2015-05-12 |
EP1419849A1 (en) | 2004-05-19 |
US6793457B2 (en) | 2004-09-21 |
BR0305595A (pt) | 2004-06-22 |
CA2448465C (en) | 2012-02-07 |
DE60321528D1 (de) | 2008-07-24 |
EP1419849B1 (en) | 2008-06-11 |
US20040096322A1 (en) | 2004-05-20 |
JP4474146B2 (ja) | 2010-06-02 |
CA2448465A1 (en) | 2004-05-15 |
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