JP6131010B2 - 金属ファンブレードプラットフォーム - Google Patents
金属ファンブレードプラットフォーム Download PDFInfo
- Publication number
- JP6131010B2 JP6131010B2 JP2012180696A JP2012180696A JP6131010B2 JP 6131010 B2 JP6131010 B2 JP 6131010B2 JP 2012180696 A JP2012180696 A JP 2012180696A JP 2012180696 A JP2012180696 A JP 2012180696A JP 6131010 B2 JP6131010 B2 JP 6131010B2
- Authority
- JP
- Japan
- Prior art keywords
- fan
- platform
- rotor assembly
- wing
- fan rotor
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- 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
- 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- 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)
Description
12 ファン組立体
14 ファンシャフト
16 ロータディスク
18 ロータブレード
20 前端
22 後端
24 半径方向外側表面
26 低圧圧縮機又はブースタ
28 シャフト
30 ボルト
32 スピナー
34 プラットフォーム
Claims (9)
- ファンロータ組立体であって、
ダブテールスロット(94)の環状アレイを含むロータ(16)と、
前記ロータ(16)のダブテールスロット(94)の1つに係合されるダブテール(96)と、前記ダブテール(96)から半径方向外向きに延びる翼形部とを各々が有するファンブレード(18)のアレイと、
を備え、前記ファンブレード(18)の隣接するファンブレード間に複数のスペースが存在し、
前記ファンロータ組立体が更に、前記隣接するブレード間のスペース内に配置されるプラットフォーム(34)のアレイを備え、該プラットフォーム(34)が、
互いに反対側にある前端及び後端と、互いに反対側にある横方向の縁部とを有する金属弓形本体(40)と、
前記横方向縁部から横方向に且つファンブレード(18)に向かって前記本体(40)を越えて前記ロータから離れるように半径方向外側に延びる脆弱ウィング(42)のペアと、
を含み、
前記プラットフォーム(34)の各々の各横方向縁部と、前記隣接するファンブレード(18)との間にギャップが存在する、
ファンロータ組立体。 - 前記本体(40)及び前記ウィング(42)が単体構造部材の一部を形成する、請求項1に記載のファンロータ組立体。
- 前記横方向縁部の一方が凹曲面を有し、前記横方向縁部の他方が凸曲面を有する、請求項1又は2に記載のファンロータ組立体。
- 前記ウィング(42)の前記ペアの一方が凹曲面を有し該ペアの他方が凸曲面を有する、請求項1〜3の何れかに記載のファンロータ組立体。
- 前記各ウィング(42)と前記本体(40)の外側表面との間の傾斜角が90度よりも大きく180度よりも小さい、請求項1〜4の何れかに記載のファンロータ組立体。
- 前記各ウィング(42)の根元の厚みに対する前記各ウィング(42)の先端の厚みの比が1よりも小さい、請求項1〜5の何れかに記載のファンロータ組立体。
- 前記各ウィング(42)の半径方向長さが、前記ギャップのサイズよりも実質的に大きい、請求項1〜6の何れかに記載のファンロータ組立体。
- 前記各ウィング(42)の各々の先端と前記隣接するファンブレード(18)との間に配置される弾性シール部材(62)を更に備える、請求項1〜7の何れかに記載のファンロータ組立体。
- 前記各プラットフォーム(34)が、該プラットフォーム(34)の前端から軸方向外向きに延びる前方取付フランジ(64)と、前記プラットフォーム(34)の後端から軸方向外向きに延びる後方取付フランジ(66)とを通じて前記ロータ(16)に取り付けられる、請求項1〜8の何れかに記載のファンロータ組立体。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/214,718 US8777576B2 (en) | 2011-08-22 | 2011-08-22 | Metallic fan blade platform |
US13/214,718 | 2011-08-22 |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2013044328A JP2013044328A (ja) | 2013-03-04 |
JP2013044328A5 JP2013044328A5 (ja) | 2015-10-01 |
JP6131010B2 true JP6131010B2 (ja) | 2017-05-17 |
Family
ID=46829632
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2012180696A Active JP6131010B2 (ja) | 2011-08-22 | 2012-08-17 | 金属ファンブレードプラットフォーム |
Country Status (4)
Country | Link |
---|---|
US (1) | US8777576B2 (ja) |
EP (1) | EP2562362A3 (ja) |
JP (1) | JP6131010B2 (ja) |
CA (1) | CA2786362A1 (ja) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2992676B1 (fr) * | 2012-06-29 | 2014-08-01 | Snecma | Plateforme inter-aubes pour une soufflante, rotor d'une soufflante et procede de fabrication associe |
US9366185B2 (en) | 2012-09-28 | 2016-06-14 | United Technologies Corporation | Flexible connection between a wall and a case of a turbine engine |
EP2971524A4 (en) | 2013-03-12 | 2016-11-02 | United Technologies Corp | T-SHAPED TURN PREVENTION LASTS FOR A PLATFORM EDGE EDGE |
US9845699B2 (en) * | 2013-03-15 | 2017-12-19 | Gkn Aerospace Services Structures Corp. | Fan spacer having unitary over molded feature |
FR3022890B1 (fr) | 2014-06-25 | 2018-01-05 | Snecma | Turbomachine comportant un moyen de decouplage d'une soufflante |
US10024234B2 (en) * | 2014-09-08 | 2018-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Panels of a fan of a gas turbine |
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 |
FR3038653B1 (fr) * | 2015-07-08 | 2017-08-04 | Snecma | Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante |
US20170058916A1 (en) * | 2015-09-01 | 2017-03-02 | United Technologies Corporation | Gas turbine fan fairing platform and method of fairing a root leading edge of a fan blade of a gas turbine engine |
US10584592B2 (en) * | 2015-11-23 | 2020-03-10 | United Technologies Corporation | Platform for an airfoil having bowed sidewalls |
FR3052484B1 (fr) * | 2016-06-08 | 2020-04-24 | Safran Aircraft Engines | Rotor resistant aux impacts |
GB201813666D0 (en) * | 2018-08-22 | 2018-10-03 | Rolls Royce Plc | Fan blade |
US11359500B2 (en) * | 2018-10-18 | 2022-06-14 | Raytheon Technologies Corporation | Rotor assembly with structural platforms for gas turbine engines |
FR3087831B1 (fr) * | 2018-10-30 | 2022-06-24 | Safran Aircraft Engines | Aube comprenant une structure en materiau composite et une piece de raidissement metallique |
FR3097904B1 (fr) * | 2019-06-26 | 2021-06-11 | Safran Aircraft Engines | Plateforme inter-aube avec caisson sacrificiel |
Family Cites Families (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3294364A (en) | 1962-01-02 | 1966-12-27 | Gen Electric | Rotor assembly |
GB1232506A (ja) | 1969-10-28 | 1971-05-19 | ||
US3625634A (en) | 1969-12-10 | 1971-12-07 | Gen Motors Corp | Turbomachine rotor |
GB2006883B (en) | 1977-10-27 | 1982-02-24 | Rolls Royce | Fan or compressor stage for a gas turbine engine |
GB2171151B (en) | 1985-02-20 | 1988-05-18 | Rolls Royce | Rotors for gas turbine engines |
FR2639402B1 (fr) | 1988-11-23 | 1990-12-28 | Snecma | Disque ailete de rotor de turbomachine |
US5277548A (en) | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
GB9208409D0 (en) | 1992-04-16 | 1992-06-03 | Rolls Royce Plc | Rotors for gas turbine engines |
US5375978A (en) | 1992-05-01 | 1994-12-27 | General Electric Company | Foreign object damage resistant composite blade and manufacture |
GB9209895D0 (en) | 1992-05-07 | 1992-06-24 | Rolls Royce Plc | Rotors for gas turbine engines |
US5281096A (en) | 1992-09-10 | 1994-01-25 | General Electric Company | Fan assembly having lightweight platforms |
GB9602129D0 (en) | 1996-02-02 | 1996-04-03 | Rolls Royce Plc | Rotors for gas turbine engines |
US5820338A (en) | 1997-04-24 | 1998-10-13 | United Technologies Corporation | Fan blade interplatform seal |
US6217283B1 (en) * | 1999-04-20 | 2001-04-17 | General Electric Company | Composite fan platform |
US6561761B1 (en) * | 2000-02-18 | 2003-05-13 | General Electric Company | Fluted compressor flowpath |
US6447250B1 (en) | 2000-11-27 | 2002-09-10 | General Electric Company | Non-integral fan platform |
FR2831207B1 (fr) * | 2001-10-24 | 2004-06-04 | Snecma Moteurs | Plates-formes pour aubes d'un ensemble rotatif |
US6991428B2 (en) | 2003-06-12 | 2006-01-31 | Pratt & Whitney Canada Corp. | Fan blade platform feature for improved blade-off performance |
FR2858353B1 (fr) | 2003-07-31 | 2005-10-07 | Snecma Moteurs | Plate-forme inter-aubes a pions de fixation a flexion et contraintes de cisaillement variables, pour un disque de support d'aubes de turboreacteur |
FR2858351B1 (fr) * | 2003-07-31 | 2006-01-13 | Snecma Moteurs | Plate-forme inter-aubes a flechissement lateral, pour un support d'aubes de turboreacteur |
FR2914008B1 (fr) * | 2007-03-21 | 2009-10-09 | Snecma Sa | Ensemble rotatif d'une soufflante de turbomachine |
-
2011
- 2011-08-22 US US13/214,718 patent/US8777576B2/en active Active
-
2012
- 2012-08-10 EP EP12179998.5A patent/EP2562362A3/en not_active Withdrawn
- 2012-08-16 CA CA2786362A patent/CA2786362A1/en active Pending
- 2012-08-17 JP JP2012180696A patent/JP6131010B2/ja active Active
Also Published As
Publication number | Publication date |
---|---|
CA2786362A1 (en) | 2013-02-22 |
EP2562362A2 (en) | 2013-02-27 |
EP2562362A3 (en) | 2018-01-03 |
US8777576B2 (en) | 2014-07-15 |
JP2013044328A (ja) | 2013-03-04 |
US20130052012A1 (en) | 2013-02-28 |
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