KR20040034516A - 압축기 블레이드 및 압축기 블레이드의 에어포일부의 전연제거 방법 - Google Patents
압축기 블레이드 및 압축기 블레이드의 에어포일부의 전연제거 방법 Download PDFInfo
- Publication number
- KR20040034516A KR20040034516A KR1020030072517A KR20030072517A KR20040034516A KR 20040034516 A KR20040034516 A KR 20040034516A KR 1020030072517 A KR1020030072517 A KR 1020030072517A KR 20030072517 A KR20030072517 A KR 20030072517A KR 20040034516 A KR20040034516 A KR 20040034516A
- Authority
- KR
- South Korea
- Prior art keywords
- leading edge
- blade
- undercut
- compressor blade
- compressor
- Prior art date
Links
Classifications
-
- 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
- F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- 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
- 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
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims (10)
- 압축기 블레이드(10)에 있어서,전연(20)을 갖는 에어포일부(12)와,반경방향 내측 부착부(16)와,상기 에어포일부와 상기 부착부 사이의 플랫폼(14)을 포함하며,재료가 상기 부착부로부터 제거되어 그 전방면(26)에 언더컷(18)이 형성됨으로써, 상기 플랫폼(14) 및 상기 에어포일부(12)의 전연(20)의 반경방향 내측에 오버행이 제공되는압축기 블레이드.
- 제 1 항에 있어서,압축기 휠에 조립될 때, 상기 언더컷에 의해 형성된 간극은 스페이서(22)에 의해 채워지는압축기 블레이드.
- 제 2 항에 있어서,상기 스페이서(22)는 상기 부착부로부터 제거된 상기 재료를 포함하는압축기 블레이드.
- 제 2 항에 있어서,상기 스페이서는 부착부와 같거나 또는 다른 재료로 구성된 별개의 구성요소(22)를 포함하는압축기 블레이드.
- 제 1 항에 있어서,상기 언더컷(18)은 약 0.5" 내지 약 1.0"의 깊이를 갖는압축기 블레이드.
- 제 1 항에 있어서,상기 언더컷(18)은 적어도 상기 에어포일부(12)의 전연(20)까지 반경방향으로 연장되는압축기 블레이드.
- 압축기 블레이드의 에어포일부의 전연을 제거하는 방법에 있어서,① 전연(20)을 갖는 에어포일부(12)와, 플랫폼(14)과, 압축기 휠에 블레이드를 고정시키는 부착부(16)를 구비하는 상기 블레이드(10)를 제공하는 단계와,② 상기 에어포일부(12)의 전연(20)의 반경방향 내측으로 언더컷(18)을 형성하도록 상기 부착부로부터 상기 재료를 제거하는 단계를 포함하는압축기 블레이드의 에어포일부의 전연 제거 방법.
- 제 7 항에 있어서,압축기 휠상에 조립될 때, 상기 언더컷에 의해 형성된 간극이 스페이서(22)에 의해 채워지는압축기 블레이드의 에어포일부의 전연 제거 방법.
- 제 7 항에 있어서,상기 스페이서(22)는 상기 부착부로부터 제거된 상기 재료를 포함하는압축기 블레이드의 에어포일부의 전연 제거 방법.
- 제 7 항에 있어서,상기 스페이서(22)는 상기 부착부와 같거나 또는 다른 재료로 구성된 별개의 구성요소를 포함하는압축기 블레이드의 에어포일부의 전연 제거 방법.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/065,453 US6769877B2 (en) | 2002-10-18 | 2002-10-18 | Undercut leading edge for compressor blades and related method |
US10/065,453 | 2002-10-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
KR20040034516A true KR20040034516A (ko) | 2004-04-28 |
KR100847942B1 KR100847942B1 (ko) | 2008-07-22 |
Family
ID=32041320
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
KR1020030072517A KR100847942B1 (ko) | 2002-10-18 | 2003-10-17 | 조립체 및 압축기 블레이드의 에어포일부의 전연 언로딩 방법 |
Country Status (4)
Country | Link |
---|---|
US (1) | US6769877B2 (ko) |
EP (1) | EP1411208B1 (ko) |
JP (1) | JP2004138067A (ko) |
KR (1) | KR100847942B1 (ko) |
Families Citing this family (17)
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US6902376B2 (en) * | 2002-12-26 | 2005-06-07 | General Electric Company | Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
US7121803B2 (en) * | 2002-12-26 | 2006-10-17 | General Electric Company | Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
US20040213672A1 (en) * | 2003-04-25 | 2004-10-28 | Gautreau James Charles | Undercut leading edge for compressor blades and related method |
FR2851285B1 (fr) * | 2003-02-13 | 2007-03-16 | Snecma Moteurs | Realisation de turbines pour turbomachines ayant des aubes a frequences de resonance ajustees differentes et procede d'ajustement de la frequence de resonance d'une aube de turbine |
US7252481B2 (en) * | 2004-05-14 | 2007-08-07 | Pratt & Whitney Canada Corp. | Natural frequency tuning of gas turbine engine blades |
US7156621B2 (en) * | 2004-05-14 | 2007-01-02 | Pratt & Whitney Canada Corp. | Blade fixing relief mismatch |
US7549846B2 (en) * | 2005-08-03 | 2009-06-23 | United Technologies Corporation | Turbine blades |
FR2896289B1 (fr) * | 2006-01-13 | 2008-03-28 | Snecma Sa | Masselotte d'equilibrage, disque de rotor en etant equipe, rotor et moteur d'aeronef les comportant |
US7594799B2 (en) * | 2006-09-13 | 2009-09-29 | General Electric Company | Undercut fillet radius for blade dovetails |
US20090297351A1 (en) * | 2008-05-28 | 2009-12-03 | General Electric Company | Compressor rotor blade undercut |
US8834123B2 (en) * | 2009-12-29 | 2014-09-16 | Rolls-Royce Corporation | Turbomachinery component |
FR2963383B1 (fr) * | 2010-07-27 | 2016-09-09 | Snecma | Aube de turbomachine, rotor, turbine basse pression et turbomachine equipes d'une telle aube |
US8813331B2 (en) | 2011-03-29 | 2014-08-26 | General Electric Company | Process of preparing a turbine rotor wheel, a repair wheel for a turbine rotor wheel, and a turbine rotor wheel |
GB201203303D0 (en) * | 2012-02-27 | 2012-04-11 | Rolls Royce Plc | Balancing of rotor |
US9617860B2 (en) | 2012-12-20 | 2017-04-11 | United Technologies Corporation | Fan blades for gas turbine engines with reduced stress concentration at leading edge |
EP2853686A1 (de) * | 2013-09-27 | 2015-04-01 | Siemens Aktiengesellschaft | Turbinenschaufel, und zugehörige Herstellungsverfahren, Stator, Rotor, Turbine und Kraftwerksanlage |
US10450872B2 (en) | 2016-11-08 | 2019-10-22 | Rolls-Royce Corporation | Undercut on airfoil coversheet support member |
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-
2002
- 2002-10-18 US US10/065,453 patent/US6769877B2/en not_active Expired - Fee Related
-
2003
- 2003-10-15 EP EP03256495A patent/EP1411208B1/en not_active Expired - Lifetime
- 2003-10-17 KR KR1020030072517A patent/KR100847942B1/ko active IP Right Grant
- 2003-10-17 JP JP2003357147A patent/JP2004138067A/ja active Pending
Also Published As
Publication number | Publication date |
---|---|
US20040076521A1 (en) | 2004-04-22 |
JP2004138067A (ja) | 2004-05-13 |
EP1411208A1 (en) | 2004-04-21 |
EP1411208B1 (en) | 2007-09-26 |
KR100847942B1 (ko) | 2008-07-22 |
US6769877B2 (en) | 2004-08-03 |
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