JP4074244B2 - シーリング要素を備えたタービンブレード - Google Patents
シーリング要素を備えたタービンブレード Download PDFInfo
- Publication number
- JP4074244B2 JP4074244B2 JP2003500391A JP2003500391A JP4074244B2 JP 4074244 B2 JP4074244 B2 JP 4074244B2 JP 2003500391 A JP2003500391 A JP 2003500391A JP 2003500391 A JP2003500391 A JP 2003500391A JP 4074244 B2 JP4074244 B2 JP 4074244B2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- end portion
- wiper
- pressure side
- axis
- 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.)
- Expired - Lifetime
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Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Description
Claims (7)
- ブレードの軸(XX’)の両側に配置された圧力側(8)および吸引側(10)を有する、タービンの可動回転子段のブレード(2)であって、前記ブレード(2)が、外周端部に位置するヘッド(6)と、前記ヘッド(6)上に形成された少なくとも1つのシーリングワイパ(12、14)とをさらに含み、前記シーリングワイパ(12、14)が、圧力側および吸引側(8、10)を横断して配置され、吸引側(10)に第1の端部分(16、18)を与え、圧力側(8)に第2の端部分(20、22)を与え、前記第1の端部分(16、18)のブレード基部(4)からの高さが、前記第2の端部分(20、22)のブレード基部(4)からの高さよりも大きく、前記ワイパが、前記第1および第2の端部分(16、18;20、22)の間にワイパ先端部(26)を与え、
前記ワイパ先端部(26)が、前記第1および第2の端部分の間に延在する凸状の表面(28)を与えることを特徴とする、ブレード(2)。 - 前記凸状の表面(28)の断面が、中心軸(xx’)、中心(O)、半径(R)を有する円形であることを特徴とする、請求項1に記載のブレード(2)。
- 前記中心軸(xx’)が、圧力側(8)から吸引側(10)へ向けられた角度(α)だけブレード軸(XX’)から偏位し、中心(O)が、ブレード軸(XX’)に垂直方向に測定された距離(L)だけ偏位したことを特徴とする、請求項2に記載のブレード(2)。
- 前記距離(L)が、少なくとも1ピッチステップの半分であり、1ピッチステップの半分が、前記第1の端部分(16、18)と前記第2の端部分(20、22)との間隔の半分に相当することを特徴とする、請求項3に記載のブレード(2)。
- 前記第1の端部分(16、18)と前記第2の端部分(20、22)との間の高低差(d)が、少なくとも0.2mmであることを特徴とする、請求項1から4のいずれか一項に記載のブレード(2)。
- 2つのワイパ(12、14)を備えることを特徴とする、請求項1から5のいずれか一項に記載のブレード(2)。
- 両方のワイパ(12、14)が、実質的に平行であることを特徴とする、請求項6に記載のブレード(2)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0107122A FR2825411B1 (fr) | 2001-05-31 | 2001-05-31 | Aube de turbine avec lechette d'etancheite |
PCT/FR2002/001812 WO2002097241A1 (fr) | 2001-05-31 | 2002-05-30 | Aube de turbine avec lechette d'etancheite |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2004526899A JP2004526899A (ja) | 2004-09-02 |
JP4074244B2 true JP4074244B2 (ja) | 2008-04-09 |
Family
ID=8863806
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2003500391A Expired - Lifetime JP4074244B2 (ja) | 2001-05-31 | 2002-05-30 | シーリング要素を備えたタービンブレード |
Country Status (9)
Country | Link |
---|---|
US (1) | US6939104B2 (ja) |
EP (1) | EP1262633B1 (ja) |
JP (1) | JP4074244B2 (ja) |
CA (1) | CA2448802C (ja) |
DE (1) | DE60203214T2 (ja) |
ES (1) | ES2240670T3 (ja) |
FR (1) | FR2825411B1 (ja) |
RU (1) | RU2296226C2 (ja) |
WO (1) | WO2002097241A1 (ja) |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004025321A1 (de) | 2004-05-19 | 2005-12-08 | Alstom Technology Ltd | Strömungsmaschinenschaufel |
US7549841B1 (en) | 2005-09-03 | 2009-06-23 | Florida Turbine Technologies, Inc. | Pressure balanced centrifugal tip seal |
FR2893268B1 (fr) * | 2005-11-15 | 2008-02-08 | Snecma Sa | Procede de realisation d'un rebord situe a l'extremite libre d'une aube, aube obtenue par ce procede et turbomachine equipee de cette aube |
US20090097979A1 (en) * | 2007-07-31 | 2009-04-16 | Omer Duane Erdmann | Rotor blade |
FR2923524B1 (fr) * | 2007-11-12 | 2013-12-06 | Snecma | Aube metallique fabriquee par moulage et procede de fabrication de l'aube |
DE102008061800A1 (de) * | 2008-12-11 | 2010-06-17 | Rolls-Royce Deutschland Ltd & Co Kg | Segmentierte Dichtlippen für Labyrinthdichtungsringe |
FR2950104B1 (fr) * | 2009-09-11 | 2011-12-09 | Snecma | Roue de turbomachine |
US8613596B2 (en) * | 2009-12-28 | 2013-12-24 | Rolls-Royce Corporation | Vane assembly having a vane end seal |
US9151166B2 (en) | 2010-06-07 | 2015-10-06 | Rolls-Royce North American Technologies, Inc. | Composite gas turbine engine component |
EP2412927A1 (en) * | 2010-07-29 | 2012-02-01 | Alstom Technology Ltd | Turbine blade |
RU2010150602A (ru) * | 2010-12-09 | 2012-06-20 | Альстом Текнолоджи Лтд (Ch) | Бандаж лопатки ротора |
EP2604797B1 (de) * | 2011-12-13 | 2020-01-22 | MTU Aero Engines GmbH | Laufschaufel mit einer Rippenanordnung mit abrasiver Beschichtung |
FR2985759B1 (fr) * | 2012-01-17 | 2014-03-07 | Snecma | Aube mobile de turbomachine |
US20130230379A1 (en) * | 2012-03-01 | 2013-09-05 | General Electric Company | Rotating turbomachine component having a tip leakage flow guide |
CN102926819A (zh) * | 2012-10-23 | 2013-02-13 | 如皋透平叶片制造有限公司 | 一种汽轮机叶片防窜动叶冠 |
FR3001759B1 (fr) | 2013-02-07 | 2015-01-16 | Snecma | Rouge aubagee de turbomachine |
US10167729B2 (en) | 2013-03-15 | 2019-01-01 | United Technologies Corporation | Knife edge with increased crack propagation life |
FR3072121B1 (fr) * | 2017-10-06 | 2021-07-30 | Safran Aircraft Engines | Dispositif d'etancheite entre rotor et stator de turbomachine |
FR3073595B1 (fr) | 2017-11-15 | 2020-02-07 | Safran Helicopter Engines | Joint a labyrinthe comprenant une lechette dotee d'un deflecteur |
GB201801296D0 (en) * | 2018-01-26 | 2018-03-14 | Rolls Royce Plc | Circumferental seal |
FR3095025B1 (fr) * | 2019-04-12 | 2021-03-05 | Safran Aircraft Engines | Joint d’étanchéité à labyrinthe comportant un élément abradable à densité variable de cellules |
FR3128970A1 (fr) | 2021-11-05 | 2023-05-12 | Safran Aircraft Engines | Dispositif d’etancheite a labyrinthe pour une turbomachine d’aeronef |
FR3139856B1 (fr) * | 2022-09-21 | 2024-09-06 | Safran Aircraft Engines | Roue de turbomachine |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1159965B (de) * | 1961-08-10 | 1963-12-27 | Bbc Brown Boveri & Cie | Einrichtung zur Schwingungsdaempfung an einem Turbinen- oder Verdichter-Schaufelkranz |
US3339933A (en) * | 1965-02-24 | 1967-09-05 | Gen Electric | Rotary seal |
GB1194061A (en) * | 1968-01-17 | 1970-06-10 | Rolls Royce | Improvements relating to Pressure Exchanger Rotors |
SU792014A1 (ru) * | 1978-12-13 | 1980-12-30 | Предприятие П/Я М-5906 | Лабиринтное уплотнение |
US4576551A (en) * | 1982-06-17 | 1986-03-18 | The Garrett Corporation | Turbo machine blading |
US4822248A (en) * | 1987-04-15 | 1989-04-18 | Metallurgical Industries, Inc. | Rebuilt shrouded turbine blade and method of rebuilding the same |
FR2615254A1 (fr) * | 1987-05-13 | 1988-11-18 | Snecma | Aube mobile de soufflante comportant une depouille en extremite |
DE4015206C1 (ja) * | 1990-05-11 | 1991-10-17 | Mtu Muenchen Gmbh | |
JP2001055902A (ja) * | 1999-08-18 | 2001-02-27 | Toshiba Corp | タービン動翼 |
DE10047307A1 (de) * | 2000-09-25 | 2002-08-01 | Alstom Switzerland Ltd | Dichtungsanordnung |
-
2001
- 2001-05-31 FR FR0107122A patent/FR2825411B1/fr not_active Expired - Fee Related
-
2002
- 2002-05-30 RU RU2003134537/06A patent/RU2296226C2/ru active
- 2002-05-30 US US10/479,180 patent/US6939104B2/en not_active Expired - Lifetime
- 2002-05-30 EP EP02291315A patent/EP1262633B1/fr not_active Expired - Lifetime
- 2002-05-30 WO PCT/FR2002/001812 patent/WO2002097241A1/fr active Application Filing
- 2002-05-30 DE DE60203214T patent/DE60203214T2/de not_active Expired - Lifetime
- 2002-05-30 CA CA002448802A patent/CA2448802C/fr not_active Expired - Lifetime
- 2002-05-30 JP JP2003500391A patent/JP4074244B2/ja not_active Expired - Lifetime
- 2002-05-30 ES ES02291315T patent/ES2240670T3/es not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
CA2448802A1 (fr) | 2002-12-05 |
DE60203214T2 (de) | 2006-03-23 |
EP1262633A1 (fr) | 2002-12-04 |
US6939104B2 (en) | 2005-09-06 |
EP1262633B1 (fr) | 2005-03-16 |
RU2296226C2 (ru) | 2007-03-27 |
JP2004526899A (ja) | 2004-09-02 |
RU2003134537A (ru) | 2005-05-10 |
ES2240670T3 (es) | 2005-10-16 |
FR2825411A1 (fr) | 2002-12-06 |
FR2825411B1 (fr) | 2003-09-19 |
US20040146404A1 (en) | 2004-07-29 |
DE60203214D1 (de) | 2005-04-21 |
WO2002097241A1 (fr) | 2002-12-05 |
CA2448802C (fr) | 2009-01-13 |
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