FR3048997B1 - Plateforme d'aube et disque de soufflante de turbomachine aeronautique - Google Patents
Plateforme d'aube et disque de soufflante de turbomachine aeronautique Download PDFInfo
- Publication number
- FR3048997B1 FR3048997B1 FR1652401A FR1652401A FR3048997B1 FR 3048997 B1 FR3048997 B1 FR 3048997B1 FR 1652401 A FR1652401 A FR 1652401A FR 1652401 A FR1652401 A FR 1652401A FR 3048997 B1 FR3048997 B1 FR 3048997B1
- Authority
- FR
- France
- Prior art keywords
- bottom wall
- platform
- disc
- blade platform
- axial
- 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.)
- Active
Links
- 230000014759 maintenance of location Effects 0.000 abstract 3
- 210000003462 vein Anatomy 0.000 abstract 3
- 238000011144 upstream manufacturing Methods 0.000 abstract 1
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
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
- F05D2230/60—Assembly methods
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Plateforme (30) apte à être intercalée entre deux aubes (20) adjacentes d'une soufflante (2), et comportant une paroi de veine (34), une paroi de fond (36) et des surfaces de rétention axiale et radiale. La paroi de veine (34) définit une veine d'écoulement d'air de soufflante (2), la paroi de fond (36) présente une surface principale (36a) pour prendre appui sur un disque (40) de soufflante, et les surfaces de rétention axiale et radiale sont disposées sur deux extrémités axiales de la plateforme (30). La surface de rétention radiale (38), disposée sur l'extrémité axiale amont de la plateforme (30), est décalée radialement, dans la direction d'appui de la paroi de fond (36) sur le disque (40), par rapport à la surface principale (36a) de la paroi de fond (36).
Priority Applications (9)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1652401A FR3048997B1 (fr) | 2016-03-21 | 2016-03-21 | Plateforme d'aube et disque de soufflante de turbomachine aeronautique |
PCT/FR2017/050649 WO2017162975A1 (fr) | 2016-03-21 | 2017-03-20 | Plateforme, disque et ensemble de soufflante |
CA3018448A CA3018448A1 (fr) | 2016-03-21 | 2017-03-20 | Plateforme, disque et ensemble de soufflante |
RU2018136891A RU2728547C2 (ru) | 2016-03-21 | 2017-03-20 | Платформа лопасти и диск вентилятора для авиационного турбинного двигателя |
JP2018549497A JP7164435B2 (ja) | 2016-03-21 | 2017-03-20 | 航空機タービンエンジン用の翼台座及びファンディスク |
EP17716956.2A EP3433469B1 (fr) | 2016-03-21 | 2017-03-20 | Plateforme, ensemble pour soufflante et soufflante |
BR112018069179-8A BR112018069179B1 (pt) | 2016-03-21 | 2017-03-20 | Plataforma apta a ser interposta entre duas pás adjacentes de um ventilador, conjunto, e, ventilador de turbomáquina |
CN201780019114.2A CN108884720B (zh) | 2016-03-21 | 2017-03-20 | 航空涡轮发动机的叶片平台和风扇盘 |
US16/086,492 US11021973B2 (en) | 2016-03-21 | 2017-03-20 | Blade platform and a fan disk for an aviation turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1652401 | 2016-03-21 | ||
FR1652401A FR3048997B1 (fr) | 2016-03-21 | 2016-03-21 | Plateforme d'aube et disque de soufflante de turbomachine aeronautique |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3048997A1 FR3048997A1 (fr) | 2017-09-22 |
FR3048997B1 true FR3048997B1 (fr) | 2020-03-27 |
Family
ID=57184524
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1652401A Active FR3048997B1 (fr) | 2016-03-21 | 2016-03-21 | Plateforme d'aube et disque de soufflante de turbomachine aeronautique |
Country Status (8)
Country | Link |
---|---|
US (1) | US11021973B2 (fr) |
EP (1) | EP3433469B1 (fr) |
JP (1) | JP7164435B2 (fr) |
CN (1) | CN108884720B (fr) |
CA (1) | CA3018448A1 (fr) |
FR (1) | FR3048997B1 (fr) |
RU (1) | RU2728547C2 (fr) |
WO (1) | WO2017162975A1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3089548B1 (fr) * | 2018-12-07 | 2021-03-19 | Safran Aircraft Engines | Soufflante comprenant une plateforme inter-aubes fixee a l’amont par une virole |
FR3120813B1 (fr) | 2021-03-16 | 2024-02-09 | Safran Aircraft Engines | Procédé de fabrication d’un disque de soufflante avec partie en fabrication additive |
Family Cites Families (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2006883B (en) * | 1977-10-27 | 1982-02-24 | Rolls Royce | Fan or compressor stage for a gas turbine engine |
US4265595A (en) * | 1979-01-02 | 1981-05-05 | General Electric Company | Turbomachinery blade retaining assembly |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
US5281096A (en) * | 1992-09-10 | 1994-01-25 | General Electric Company | Fan assembly having lightweight platforms |
FR2814495B1 (fr) * | 2000-09-28 | 2003-01-17 | Snecma Moteurs | Systeme de retention amont pour aubes et plates-formes de soufflante |
US6520742B1 (en) * | 2000-11-27 | 2003-02-18 | General Electric Company | Circular arc multi-bore fan disk |
US6447250B1 (en) * | 2000-11-27 | 2002-09-10 | General Electric Company | Non-integral fan platform |
US6481971B1 (en) * | 2000-11-27 | 2002-11-19 | General Electric Company | Blade spacer |
US6634863B1 (en) * | 2000-11-27 | 2003-10-21 | General Electric Company | Circular arc multi-bore fan disk assembly |
US6764282B2 (en) * | 2001-11-14 | 2004-07-20 | United Technologies Corporation | Blade for turbine engine |
JP4045993B2 (ja) * | 2003-03-28 | 2008-02-13 | 株式会社Ihi | ファン静翼、航空エンジン用ファン、及び航空エンジン |
JP4807113B2 (ja) * | 2006-03-14 | 2011-11-02 | 株式会社Ihi | ファンのダブテール構造 |
FR2913734B1 (fr) * | 2007-03-16 | 2009-05-01 | Snecma Sa | Soufflante de turbomachine |
FR2930595B1 (fr) * | 2008-04-24 | 2011-10-14 | Snecma | Rotor de soufflante d'une turbomachine ou d'un moteur d'essai |
FR2931871B1 (fr) * | 2008-05-29 | 2011-08-19 | Snecma | Rotor de soufflante pour une turbomachine. |
FR2949142B1 (fr) * | 2009-08-11 | 2011-10-14 | Snecma | Cale amortisseuse de vibrations pour aube de soufflante |
US8435006B2 (en) * | 2009-09-30 | 2013-05-07 | Rolls-Royce Corporation | Fan |
US8353161B2 (en) * | 2010-04-19 | 2013-01-15 | Honeywell International Inc. | High diffusion turbine wheel with hub bulb |
GB2484988B (en) * | 2010-11-01 | 2013-08-14 | Rolls Royce Plc | Annulus filler |
US8827651B2 (en) * | 2010-11-01 | 2014-09-09 | Rolls-Royce Plc | Annulus filler |
GB201020857D0 (en) * | 2010-12-09 | 2011-01-26 | Rolls Royce Plc | Annulus filler |
GB201104994D0 (en) * | 2011-03-25 | 2011-05-11 | Rolls Royce Plc | a rotor having an annulus filler |
FR2974864B1 (fr) * | 2011-05-04 | 2016-05-27 | Snecma | Rotor de turbomachine avec moyen de retenue axiale des aubes |
FR2987086B1 (fr) * | 2012-02-22 | 2014-03-21 | Snecma | Joint lineaire de plateforme inter-aubes |
FR2989724B1 (fr) * | 2012-04-20 | 2015-12-25 | Snecma | Etage de turbine pour une turbomachine |
CN202645641U (zh) * | 2012-05-10 | 2013-01-02 | 中航商用航空发动机有限责任公司 | 一种轮盘 |
US9399922B2 (en) * | 2012-12-31 | 2016-07-26 | General Electric Company | Non-integral fan blade platform |
US9759226B2 (en) * | 2013-02-15 | 2017-09-12 | United Technologies Corporation | Low profile fan platform attachment |
EP2971524A4 (fr) * | 2013-03-12 | 2016-11-02 | United Technologies Corp | Volets compensateurs anti-rotation de bord d'attaque de plateforme en forme de t |
GB201314542D0 (en) * | 2013-08-14 | 2013-09-25 | Rolls Royce Plc | Annulus Filler |
DE102014217887A1 (de) * | 2014-09-08 | 2016-03-10 | Rolls-Royce Deutschland Ltd & Co Kg | Füllelemente eines Fans einer Gasturbine |
US10024234B2 (en) * | 2014-09-08 | 2018-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Panels of a fan of a gas turbine |
FR3029563B1 (fr) * | 2014-12-08 | 2020-01-17 | Safran Aircraft Engines | Plateforme a faible rapport de moyeu |
FR3033179B1 (fr) * | 2015-02-26 | 2018-07-27 | Safran Aircraft Engines | Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante |
US10605117B2 (en) * | 2015-10-08 | 2020-03-31 | General Electric Company | Fan platform for a gas turbine engine |
FR3082876B1 (fr) * | 2018-06-21 | 2021-01-22 | Safran Aircraft Engines | Soufflante comprenant une plateforme et un verrou de blocage |
-
2016
- 2016-03-21 FR FR1652401A patent/FR3048997B1/fr active Active
-
2017
- 2017-03-20 RU RU2018136891A patent/RU2728547C2/ru active
- 2017-03-20 EP EP17716956.2A patent/EP3433469B1/fr active Active
- 2017-03-20 CA CA3018448A patent/CA3018448A1/fr active Pending
- 2017-03-20 WO PCT/FR2017/050649 patent/WO2017162975A1/fr active Application Filing
- 2017-03-20 US US16/086,492 patent/US11021973B2/en active Active
- 2017-03-20 JP JP2018549497A patent/JP7164435B2/ja active Active
- 2017-03-20 CN CN201780019114.2A patent/CN108884720B/zh active Active
Also Published As
Publication number | Publication date |
---|---|
CN108884720B (zh) | 2021-11-02 |
RU2018136891A (ru) | 2020-04-22 |
BR112018069179A2 (pt) | 2019-01-29 |
RU2728547C2 (ru) | 2020-07-30 |
JP2019512639A (ja) | 2019-05-16 |
US11021973B2 (en) | 2021-06-01 |
WO2017162975A1 (fr) | 2017-09-28 |
CN108884720A (zh) | 2018-11-23 |
JP7164435B2 (ja) | 2022-11-01 |
US20190055847A1 (en) | 2019-02-21 |
EP3433469A1 (fr) | 2019-01-30 |
CA3018448A1 (fr) | 2017-09-28 |
EP3433469B1 (fr) | 2023-04-26 |
FR3048997A1 (fr) | 2017-09-22 |
RU2018136891A3 (fr) | 2020-06-03 |
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Legal Events
Date | Code | Title | Description |
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PLFP | Fee payment |
Year of fee payment: 2 |
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PLSC | Publication of the preliminary search report |
Effective date: 20170922 |
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PLFP | Fee payment |
Year of fee payment: 3 |
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CD | Change of name or company name |
Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
|
PLFP | Fee payment |
Year of fee payment: 4 |
|
PLFP | Fee payment |
Year of fee payment: 5 |
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PLFP | Fee payment |
Year of fee payment: 6 |
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PLFP | Fee payment |
Year of fee payment: 7 |
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PLFP | Fee payment |
Year of fee payment: 8 |
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PLFP | Fee payment |
Year of fee payment: 9 |