JP2012511661A - タービンエンジンのロータ内のプラットフォームのためのシール - Google Patents
タービンエンジンのロータ内のプラットフォームのためのシール Download PDFInfo
- Publication number
- JP2012511661A JP2012511661A JP2011540101A JP2011540101A JP2012511661A JP 2012511661 A JP2012511661 A JP 2012511661A JP 2011540101 A JP2011540101 A JP 2011540101A JP 2011540101 A JP2011540101 A JP 2011540101A JP 2012511661 A JP2012511661 A JP 2012511661A
- Authority
- JP
- Japan
- Prior art keywords
- seal
- platform
- rotor
- section
- downstream
- 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
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
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
-
- 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
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
Description
Claims (9)
- タービンエンジンのロータ内の2つの隣接するブレード間の中間プラットフォーム(4)のためのシール(16)にして、上流側端部と下流側端部とを有する細長形状であり、横方向に、幅方向に、接触部分、取り付け部分、および取り付け部分と接触部分との間の可撓性部分を備えるシールであって、前記シールの断面が、その両端の間で、次第に変化する形状(161、162、163、161’、162’、163’)であり、接触部分の断面が球状形状(163、163’)を有し、一端から他端に向かって次第に小さくなることを特徴とする、シール。
- 接触部分の断面が、楕円形、特に円形であることを特徴とする、請求項1に記載のシール。
- 上流側端部または下流側端部のうちの少なくとも一方が、テーパ状である、請求項1または2に記載のシール。
- 少なくとも1つの長手方向側方縁部に沿って、請求項1から3のいずれか一項に記載のシールを備える、タービンエンジンのロータの中間プラットフォーム。
- 軸方向一端が請求項2から4のいずれか一項に記載のシールを有する軸方向他端よりも大きい直径を有し、最も小さい断面が大きい方の直径側にくるようにロータのリム上に軸方向に取り付けられるように配置される、請求項4に記載のプラットフォーム。
- 上流側軸方向端部と上流側軸方向端部よりも大きい直径の下流側軸方向端部とを有し、シールが上流側ゾーンDと下流側ゾーンEとを有し、上流側ゾーンDが一定の断面およびシールの長さの1/2から2/3の長さを有し、下流側ゾーンEの断面が下流側方向に向かって次第に小さくなる、請求項5に記載のプラットフォーム。
- ターボジェットのファンロータに取り付けられるように配置された、請求項6に記載のプラットフォーム。
- 請求項6から8のいずれか一項に記載の中間プラットフォームを備える、ターボジェットエンジンのロータ。
- タービンエンジンがターボジェットのファンである、請求項8に記載のロータ。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0858539A FR2939836B1 (fr) | 2008-12-12 | 2008-12-12 | Joint d'etancheite de plateforme dans un rotor de turbomachine |
FR0858539 | 2008-12-12 | ||
PCT/EP2009/066819 WO2010066833A1 (fr) | 2008-12-12 | 2009-12-10 | Joint d'etancheite de plateforme dans un rotor de turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2012511661A true JP2012511661A (ja) | 2012-05-24 |
JP5576392B2 JP5576392B2 (ja) | 2014-08-20 |
Family
ID=40933526
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2011540101A Active JP5576392B2 (ja) | 2008-12-12 | 2009-12-10 | タービンエンジンのロータ内のプラットフォームのためのシール |
Country Status (9)
Country | Link |
---|---|
US (1) | US8827650B2 (ja) |
EP (1) | EP2368019B1 (ja) |
JP (1) | JP5576392B2 (ja) |
CN (1) | CN102245860B (ja) |
BR (1) | BRPI0923327B1 (ja) |
CA (1) | CA2745605C (ja) |
FR (1) | FR2939836B1 (ja) |
RU (1) | RU2511897C2 (ja) |
WO (1) | WO2010066833A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2015041083A1 (ja) | 2013-09-18 | 2015-03-26 | 株式会社Ihi | ターボファンエンジンのためのシール |
JP2017530290A (ja) * | 2014-08-22 | 2017-10-12 | シーメンス エナジー インコーポレイテッド | 別個のプラットフォーム支持システムを備えるモジュール式タービンブレード |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2933887B1 (fr) * | 2008-07-18 | 2010-09-17 | Snecma | Procede de reparation ou de reprise d'un disque de turbomachine et disque de turbomachine repare ou repris |
FR2945074B1 (fr) | 2009-04-29 | 2011-06-03 | Snecma | Cale d'aube de soufflante renforcee |
FR2955904B1 (fr) * | 2010-02-04 | 2012-07-20 | Snecma | Soufflante de turbomachine |
FR2992676B1 (fr) * | 2012-06-29 | 2014-08-01 | Snecma | Plateforme inter-aubes pour une soufflante, rotor d'une soufflante et procede de fabrication associe |
US20140169979A1 (en) * | 2012-12-14 | 2014-06-19 | United Technologies Corporation | Gas turbine engine fan blade platform seal |
US9759226B2 (en) | 2013-02-15 | 2017-09-12 | United Technologies Corporation | Low profile fan platform attachment |
FR3018473B1 (fr) * | 2014-03-17 | 2016-04-08 | Snecma | Procede de fabrication d'une plate-forme d'aube en materiau composite a joints integres pour soufflante de turbomachine |
US10458425B2 (en) * | 2016-06-02 | 2019-10-29 | General Electric Company | Conical load spreader for composite bolted joint |
FR3057300B1 (fr) * | 2016-10-07 | 2018-10-05 | Safran Aircraft Engines | Assemblage d'anneau mobile de turbine de turbomachine |
EP3438410B1 (en) | 2017-08-01 | 2021-09-29 | General Electric Company | Sealing system for a rotary machine |
FR3081520B1 (fr) * | 2018-05-23 | 2021-05-21 | Safran Aircraft Engines | Disque ameliore de soufflante de turbomachine |
US11028714B2 (en) * | 2018-07-16 | 2021-06-08 | Raytheon Technologies Corporation | Fan platform wedge seal |
US10557361B1 (en) * | 2018-10-16 | 2020-02-11 | United Technologies Corporation | Platform for an airfoil of a gas turbine engine |
FR3091563B1 (fr) * | 2019-01-04 | 2023-01-20 | Safran Aircraft Engines | Joint d’étanchéité amélioré de plateforme inter-aubes |
US11168572B2 (en) * | 2019-02-05 | 2021-11-09 | Raytheon Technologies Corporation | Composite gas turbine engine component |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5464326A (en) * | 1992-05-07 | 1995-11-07 | Rolls-Royce, Plc | Rotors for gas turbine engines |
JPH094410A (ja) * | 1995-06-19 | 1997-01-07 | Ishikawajima Harima Heavy Ind Co Ltd | 翼間スペーサのシール構造 |
US6514045B1 (en) * | 1999-07-06 | 2003-02-04 | Rolls-Royce Plc | Rotor seal |
US6634863B1 (en) * | 2000-11-27 | 2003-10-21 | General Electric Company | Circular arc multi-bore fan disk assembly |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3742080C2 (de) * | 1987-12-11 | 1994-07-07 | Blohm Voss Ag | Wellendichtung zum Abdichten eines flüssigen Mediums |
GB9602129D0 (en) * | 1996-02-02 | 1996-04-03 | Rolls Royce Plc | Rotors for gas turbine engines |
US6217283B1 (en) * | 1999-04-20 | 2001-04-17 | General Electric Company | Composite fan platform |
FR2835563B1 (fr) * | 2002-02-07 | 2004-04-02 | Snecma Moteurs | Agencement d'accrochage de secteurs en arc de cercle de distributeur porteur d'aubes |
US7090466B2 (en) * | 2004-09-14 | 2006-08-15 | General Electric Company | Methods and apparatus for assembling gas turbine engine rotor assemblies |
JP2006214367A (ja) * | 2005-02-04 | 2006-08-17 | Mitsubishi Heavy Ind Ltd | 動翼体 |
FR2885167B1 (fr) * | 2005-04-29 | 2007-06-29 | Snecma Moteurs Sa | Module de turbine pour moteur a turbine a gaz |
GB0611031D0 (en) * | 2006-06-06 | 2006-07-12 | Rolls Royce Plc | An aerofoil stage and a seal for use therein |
EP1914386A1 (en) * | 2006-10-17 | 2008-04-23 | Siemens Aktiengesellschaft | Turbine blade assembly |
FR2939835B1 (fr) | 2008-12-12 | 2017-06-09 | Snecma | Joint d'etancheite de plateforme dans un rotor de turbomachine, methode pour ameliorer l'etancheite entre une plateforme et une aube de turbomachine. |
-
2008
- 2008-12-12 FR FR0858539A patent/FR2939836B1/fr active Active
-
2009
- 2009-12-10 CN CN200980150196.XA patent/CN102245860B/zh active Active
- 2009-12-10 US US13/139,456 patent/US8827650B2/en active Active
- 2009-12-10 WO PCT/EP2009/066819 patent/WO2010066833A1/fr active Application Filing
- 2009-12-10 BR BRPI0923327A patent/BRPI0923327B1/pt active IP Right Grant
- 2009-12-10 JP JP2011540101A patent/JP5576392B2/ja active Active
- 2009-12-10 EP EP09799073.3A patent/EP2368019B1/fr active Active
- 2009-12-10 CA CA2745605A patent/CA2745605C/fr active Active
- 2009-12-10 RU RU2011128717/06A patent/RU2511897C2/ru active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5464326A (en) * | 1992-05-07 | 1995-11-07 | Rolls-Royce, Plc | Rotors for gas turbine engines |
JPH094410A (ja) * | 1995-06-19 | 1997-01-07 | Ishikawajima Harima Heavy Ind Co Ltd | 翼間スペーサのシール構造 |
US6514045B1 (en) * | 1999-07-06 | 2003-02-04 | Rolls-Royce Plc | Rotor seal |
US6634863B1 (en) * | 2000-11-27 | 2003-10-21 | General Electric Company | Circular arc multi-bore fan disk assembly |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2015041083A1 (ja) | 2013-09-18 | 2015-03-26 | 株式会社Ihi | ターボファンエンジンのためのシール |
US10233765B2 (en) | 2013-09-18 | 2019-03-19 | Ihi Corporation | Seal for turbofan engine |
JP2017530290A (ja) * | 2014-08-22 | 2017-10-12 | シーメンス エナジー インコーポレイテッド | 別個のプラットフォーム支持システムを備えるモジュール式タービンブレード |
Also Published As
Publication number | Publication date |
---|---|
BRPI0923327B1 (pt) | 2020-04-07 |
BRPI0923327A2 (pt) | 2016-01-12 |
CN102245860B (zh) | 2014-09-10 |
CA2745605C (fr) | 2016-11-08 |
US20110243744A1 (en) | 2011-10-06 |
FR2939836A1 (fr) | 2010-06-18 |
RU2511897C2 (ru) | 2014-04-10 |
FR2939836B1 (fr) | 2015-05-15 |
JP5576392B2 (ja) | 2014-08-20 |
WO2010066833A1 (fr) | 2010-06-17 |
CA2745605A1 (fr) | 2010-06-17 |
EP2368019A1 (fr) | 2011-09-28 |
RU2011128717A (ru) | 2013-01-20 |
EP2368019B1 (fr) | 2016-07-06 |
US8827650B2 (en) | 2014-09-09 |
CN102245860A (zh) | 2011-11-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP5576392B2 (ja) | タービンエンジンのロータ内のプラットフォームのためのシール | |
US8616850B2 (en) | Gas turbine engine blade mounting arrangement | |
CA2547176C (en) | Angled blade firtree retaining system | |
JP6514511B2 (ja) | 2つの部分スパンシュラウドおよび湾曲したダブテールを有する高翼弦動翼 | |
EP2333241B1 (en) | Duct with elongated ridge for a gas turbine engine | |
JP5264058B2 (ja) | 固定タービン翼形部 | |
US7530791B2 (en) | Turbine blade retaining apparatus | |
US9638051B2 (en) | Turbomachine bucket having angel wing for differently sized discouragers and related methods | |
CN105736460B (zh) | 结合非轴对称毂流路和分流叶片的轴向压缩机转子 | |
EP3026212B1 (en) | Blisk rim face undercut | |
JP2017082784A (ja) | スプリッタを搭載した圧縮機 | |
US10294805B2 (en) | Gas turbine engine integrally bladed rotor with asymmetrical trench fillets | |
US10408068B2 (en) | Fan blade dovetail and spacer | |
US20140255207A1 (en) | Turbine rotor blades having mid-span shrouds | |
WO2014168743A1 (en) | Integrally bladed rotor | |
US20160032734A1 (en) | Fan for a multi-flow turboshaft engine, and turboshaft engine equipped with such a fan | |
US20160010475A1 (en) | Cantilever stator with vortex initiation feature | |
JP5480965B2 (ja) | 低圧タービン | |
JP2021173283A (ja) | 翼端ポケットを有するブレード | |
US20200011188A1 (en) | Blade for a gas turbine engine | |
JP5497012B2 (ja) | 軸方向の当接部を有するタービンエンジンのための圧縮機カバー | |
CA2968386A1 (en) | Integrally bladed fan rotor |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20121207 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20131029 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20140108 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20140610 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20140703 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 5576392 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |