JP2008232147A - ターボ機械ファン - Google Patents
ターボ機械ファン Download PDFInfo
- Publication number
- JP2008232147A JP2008232147A JP2008065739A JP2008065739A JP2008232147A JP 2008232147 A JP2008232147 A JP 2008232147A JP 2008065739 A JP2008065739 A JP 2008065739A JP 2008065739 A JP2008065739 A JP 2008065739A JP 2008232147 A JP2008232147 A JP 2008232147A
- Authority
- JP
- Japan
- Prior art keywords
- disk
- platform
- upstream
- lug
- fan
- 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.)
- Pending
Links
Images
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
- F04D29/60—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
- 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
- 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
-
- 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
- F04D29/322—Blade mountings
-
- 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
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
-
- 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
-
- 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)
Abstract
【解決手段】ロータディスク(12)の周囲でスロット(23)に取り付けられるブレード(16)と、ディスク(12)の対応するラグに固着するための半径方向のラグを有するブレード間プラットフォーム(20)と、を備え、各プラットフォーム(20)が、プラットフォーム(20)のラグにおけるオリフィスおよびディスク(12)のラグにおける対応するオリフィスに挿入されるピン(64)によって、ディスク(12)に固着される。
【選択図】図1
Description
12 ディスク
14 タービンシャフト
16 ブレード
18 ファンの回転軸
20 ブレード間プラットフォーム
22 空気流
23 スロット
24 リブ
26 下流環状側板
28 下流ラグ
29 ナットおよびボルト型の手段
30 内部ファンケーシング
32 シム
36 上流環状側板
38、40 環状フランジ
42 入口円錐
44 壁
46、48、52、54 ラグ
50 補強リブ
56、58、60、62 オリフィス
64 ピン
66 ピン本体
68 ピン頭部
Claims (10)
- 根元部がロータディスクの周囲でスロットに取り付けられる複数のブレードと、ブレード根元部を取り付けるためのスロットの間で、ディスクの対応するラグに固着するための半径方向のラグを有するブレード間プラットフォームとを備え、各プラットフォームが、プラットフォームのラグにおけるオリフィスおよびディスクのラグにおける対応するオリフィスに挿入されるピンによってディスクに固着される、ターボ機械ファン。
- 各プラットフォームは、その上流端部および下流端部のそれぞれで、半径方向のラグを備える、請求項1に記載のファン。
- 各プラットフォームは、その上流端部で、ディスクの上流ラグに接触して、軸方向かつ半径方向に担持する、請求項1に記載のファン。
- 各プラットフォームは、その下流端部で、ディスクに追加されて固着される下流環状側板のラグに接触して、軸方向かつ半径方向に担持する、請求項1に記載のファン。
- ピンは、上流からプラットフォームおよびディスクのラグにおけるオリフィスに挿入され、その上流端部で、ディスクに追加されて固着される上流環状側板によって、プラットフォームの上流ラグに対して当てられて締結される頭部を備える、請求項1に記載のファン。
- 取り付けられた位置において、ピンは、ディスクの回転軸に対して斜めに延在する、請求項1に記載のファン。
- ピンは、外側に向かって下流に延在する、請求項6に記載のファン。
- 請求項1に記載のファンを備える航空機ターボファンまたはターボプロップなどのターボ機械。
- 一端部で本体より大きな直径を有する頭部に接合される実質的に円筒形の細長い直線形状の本体を備える、請求項1に記載のファンのディスクにブレード間プラットフォームを固着するためのピン。
- チタンまたは複合材料などの強力で軽量材料から製造される、請求項9に記載のピン。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0701903A FR2913734B1 (fr) | 2007-03-16 | 2007-03-16 | Soufflante de turbomachine |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2013164773A Division JP5719888B2 (ja) | 2007-03-16 | 2013-08-08 | ターボ機械ファン |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2008232147A true JP2008232147A (ja) | 2008-10-02 |
Family
ID=38657661
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008065739A Pending JP2008232147A (ja) | 2007-03-16 | 2008-03-14 | ターボ機械ファン |
JP2013164773A Active JP5719888B2 (ja) | 2007-03-16 | 2013-08-08 | ターボ機械ファン |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2013164773A Active JP5719888B2 (ja) | 2007-03-16 | 2013-08-08 | ターボ機械ファン |
Country Status (7)
Country | Link |
---|---|
US (1) | US8246310B2 (ja) |
EP (1) | EP1970537B1 (ja) |
JP (2) | JP2008232147A (ja) |
CA (1) | CA2625319C (ja) |
DE (1) | DE602008000388D1 (ja) |
FR (1) | FR2913734B1 (ja) |
RU (1) | RU2459120C2 (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2014513765A (ja) * | 2011-05-04 | 2014-06-05 | スネクマ | ブレードの軸方向保持手段を備えたターボ機械ロータ |
JP2018525558A (ja) * | 2015-07-08 | 2018-09-06 | サフラン・エアクラフト・エンジンズ | 後付けファンブレードプラットフォームを備える航空ターボ機械の回転アセンブリ |
JP2019512639A (ja) * | 2016-03-21 | 2019-05-16 | サフラン エアークラフト エンジンズ | 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 |
Families Citing this family (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2961847B1 (fr) * | 2010-06-25 | 2012-08-17 | Snecma | Roue mobile a aubes en materiau composite pour moteur a turbine a gaz a liaison pied d'aube/disque par serrage |
FR2965843B1 (fr) * | 2010-10-06 | 2012-11-09 | Snecma | Rotor pour turbomachine |
FR2974863B1 (fr) * | 2011-05-06 | 2015-10-23 | Snecma | Disque de soufflante de turbomachine |
US9303520B2 (en) | 2011-12-09 | 2016-04-05 | General Electric Company | Double fan outlet guide vane with structural platforms |
US9267386B2 (en) | 2012-06-29 | 2016-02-23 | United Technologies Corporation | Fairing assembly |
SG11201407843UA (en) | 2012-08-17 | 2015-03-30 | United Technologies Corp | Contoured flowpath surface |
US10119423B2 (en) | 2012-09-20 | 2018-11-06 | United Technologies Corporation | Gas turbine engine fan spacer platform attachments |
FR3004227B1 (fr) * | 2013-04-09 | 2016-10-21 | Snecma | Disque de soufflante pour un turboreacteur |
WO2015053848A2 (en) * | 2013-09-18 | 2015-04-16 | United Technologies Corporation | Fan platform with leading edge tab |
WO2015076900A2 (en) * | 2013-10-11 | 2015-05-28 | United Technologies Corporation | Fan rotor with integrated platform attachment |
DE102014217884A1 (de) * | 2014-09-08 | 2016-03-24 | 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 |
US9909430B2 (en) | 2014-11-13 | 2018-03-06 | Rolls-Royce North American Technologies Inc. | Turbine disk assembly including seperable platforms for blade attachment |
FR3038654B1 (fr) * | 2015-07-08 | 2017-08-04 | Snecma | Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante |
US9976426B2 (en) * | 2015-07-21 | 2018-05-22 | United Technologies Corporation | Fan platform with stiffening feature |
FR3051174B1 (fr) | 2016-05-10 | 2018-06-01 | Safran Aircraft Engines | Partie avant tournante d'un recepteur de turbomachine d'aeronef, a conception amelioree permettant un retrait repete de la pointe de cone |
FR3053083B1 (fr) * | 2016-06-22 | 2019-11-01 | Safran Aircraft Engines | Anneau de carenage de roue a aubes |
FR3057908B1 (fr) * | 2016-10-21 | 2019-11-22 | Safran Aircraft Engines | Ensemble rotatif d'une turbomachine muni d'un systeme de maintien axial d'une aube |
FR3066552B1 (fr) * | 2017-05-22 | 2021-11-19 | Safran Aircraft Engines | Assemblage sur un arbre de turbomachine d'un disque aubage monobloc et d'un rotor de compresseur basse pression a au moins deux etages d'aubes mobiles |
US10280767B2 (en) | 2017-08-29 | 2019-05-07 | United Technologies Corporation | Fan hub attachment for leading and trailing edges of fan blades |
US10612400B2 (en) * | 2017-11-27 | 2020-04-07 | United Technologies Corporation | Composite fan platform lug reinforcement |
US10781702B2 (en) * | 2018-03-08 | 2020-09-22 | Raytheon Technologies Corporation | Fan spacer for a gas turbine engine |
US10724390B2 (en) | 2018-03-16 | 2020-07-28 | General Electric Company | Collar support assembly for airfoils |
US11174741B2 (en) * | 2018-04-19 | 2021-11-16 | Raytheon Technologies Corporation | Platform for an airfoil of a gas turbine engine |
FR3082876B1 (fr) * | 2018-06-21 | 2021-01-22 | Safran Aircraft Engines | Soufflante comprenant une plateforme et un verrou de blocage |
US11092020B2 (en) | 2018-10-18 | 2021-08-17 | Raytheon Technologies Corporation | Rotor assembly for gas turbine engines |
FR3089548B1 (fr) * | 2018-12-07 | 2021-03-19 | Safran Aircraft Engines | Soufflante comprenant une plateforme inter-aubes fixee a l’amont par une virole |
FR3094400B1 (fr) | 2019-03-28 | 2022-12-16 | Safran | Rotor de soufflante pour turbomachine |
FR3107923B1 (fr) | 2020-03-03 | 2022-02-04 | Safran Aircraft Engines | Procede de fabrication d’une plateforme composite pour une soufflante de turbomachine d’aeronef |
FR3107915B1 (fr) | 2020-03-03 | 2022-02-04 | Safran Aircraft Engines | Procede de fabrication d’une plateforme composite pour une soufflante de turbomachine d’aeronef |
FR3107914B1 (fr) | 2020-03-03 | 2022-02-04 | Safran Aircraft Engines | Plateforme composite pour une soufflante de turbomachine d’aeronef |
FR3109794B1 (fr) | 2020-05-04 | 2022-08-12 | Safran Aircraft Engines | Plateforme pour un rotor de soufflante d’une turbomachine d’aéronef |
FR3109793B1 (fr) | 2020-05-04 | 2022-08-12 | Safran Aircraft Engines | Plateforme pour un rotor de soufflante d’une turbomachine d’aéronef |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2002195103A (ja) * | 2000-11-27 | 2002-07-10 | General Electric Co <Ge> | ブレード・スペーサ |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
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FR989839A (fr) * | 1949-06-28 | 1951-09-13 | Cem Comp Electro Mec | Aube pour turbo-machine |
US2751189A (en) * | 1950-09-08 | 1956-06-19 | United Aircraft Corp | Blade fastening means |
US4621979A (en) * | 1979-11-30 | 1986-11-11 | United Technologies Corporation | Fan rotor blades of turbofan engines |
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 |
FR2715968B1 (fr) * | 1994-02-10 | 1996-03-29 | Snecma | Rotor à plates-formes rapportées entre les aubes. |
GB9405473D0 (en) * | 1994-03-19 | 1994-05-04 | Rolls Royce Plc | A gas turbine engine fan blade assembly |
JP2000320492A (ja) * | 1999-05-12 | 2000-11-21 | Ishikawajima Harima Heavy Ind Co Ltd | ファンブレード支持装置用ブッシュ |
EP1124038A1 (de) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbinenschaufelanordnung |
US6422820B1 (en) * | 2000-06-30 | 2002-07-23 | General Electric Company | Corner tang fan blade |
FR2814495B1 (fr) * | 2000-09-28 | 2003-01-17 | Snecma Moteurs | Systeme de retention amont pour aubes et plates-formes de soufflante |
US6416280B1 (en) * | 2000-11-27 | 2002-07-09 | General Electric Company | One piece spinner |
US6447250B1 (en) * | 2000-11-27 | 2002-09-10 | General Electric Company | Non-integral fan platform |
US7063505B2 (en) * | 2003-02-07 | 2006-06-20 | General Electric Company | Gas turbine engine frame having struts connected to rings with morse pins |
FR2858370B1 (fr) * | 2003-07-31 | 2005-09-30 | Snecma Moteurs | Plate-forme inter-aubes allegee, pour un disque de support d'aubes de turboreacteur |
US7811053B2 (en) * | 2005-07-22 | 2010-10-12 | United Technologies Corporation | Fan rotor design for coincidence avoidance |
-
2007
- 2007-03-16 FR FR0701903A patent/FR2913734B1/fr not_active Expired - Fee Related
-
2008
- 2008-02-19 EP EP08151618A patent/EP1970537B1/fr active Active
- 2008-02-19 DE DE602008000388T patent/DE602008000388D1/de active Active
- 2008-03-12 CA CA2625319A patent/CA2625319C/fr active Active
- 2008-03-14 RU RU2008110029/06A patent/RU2459120C2/ru active
- 2008-03-14 JP JP2008065739A patent/JP2008232147A/ja active Pending
- 2008-03-14 US US12/048,550 patent/US8246310B2/en active Active
-
2013
- 2013-08-08 JP JP2013164773A patent/JP5719888B2/ja active Active
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2002195103A (ja) * | 2000-11-27 | 2002-07-10 | General Electric Co <Ge> | ブレード・スペーサ |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2014513765A (ja) * | 2011-05-04 | 2014-06-05 | スネクマ | ブレードの軸方向保持手段を備えたターボ機械ロータ |
JP2018525558A (ja) * | 2015-07-08 | 2018-09-06 | サフラン・エアクラフト・エンジンズ | 後付けファンブレードプラットフォームを備える航空ターボ機械の回転アセンブリ |
JP2019512639A (ja) * | 2016-03-21 | 2019-05-16 | サフラン エアークラフト エンジンズ | 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 |
JP7164435B2 (ja) | 2016-03-21 | 2022-11-01 | サフラン エアークラフト エンジンズ | 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 |
Also Published As
Publication number | Publication date |
---|---|
US20080226458A1 (en) | 2008-09-18 |
FR2913734B1 (fr) | 2009-05-01 |
EP1970537B1 (fr) | 2009-12-16 |
EP1970537A1 (fr) | 2008-09-17 |
DE602008000388D1 (de) | 2010-01-28 |
RU2008110029A (ru) | 2009-09-20 |
JP5719888B2 (ja) | 2015-05-20 |
RU2459120C2 (ru) | 2012-08-20 |
CA2625319C (fr) | 2015-04-28 |
CA2625319A1 (fr) | 2008-09-16 |
FR2913734A1 (fr) | 2008-09-19 |
US8246310B2 (en) | 2012-08-21 |
JP2014005834A (ja) | 2014-01-16 |
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