JP2005220906A - 第1および第2の軸受に支持される駆動シャフトと一体化したファンを有するターボジェットエンジン - Google Patents
第1および第2の軸受に支持される駆動シャフトと一体化したファンを有するターボジェットエンジン Download PDFInfo
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- JP2005220906A JP2005220906A JP2005017774A JP2005017774A JP2005220906A JP 2005220906 A JP2005220906 A JP 2005220906A JP 2005017774 A JP2005017774 A JP 2005017774A JP 2005017774 A JP2005017774 A JP 2005017774A JP 2005220906 A JP2005220906 A JP 2005220906A
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- Japan
- Prior art keywords
- bearing
- fan
- compressor shaft
- drive shaft
- jet engine
- 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.)
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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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Rolling Contact Bearings (AREA)
- Mounting Of Bearings Or Others (AREA)
Abstract
【解決手段】本発明は、固定構造体と、第1の軸受6および第2の軸受7に支持される駆動シャフト5と一体化されたファンロータ2とを備えるターボジェットエンジンに関する。本発明は、ターボジェットエンジンが、手段28を備え、該手段28は、ファンロータ2の軸方向保持手段を形成し、かつ/または非常時軸受を形成し、固定構造体の手段32、33と協働し、かつ駆動シャフト5と一体的に搭載されることを特徴とする。特に、ファン2の軸方向保持手段を形成しかつ/または非常時軸受を形成する手段が、保持ディスク28を備え、該保持ディスク28は、駆動シャフト5に搭載され、かつファン2を軸方向に保持するためのフランジ18の停止ディスク33およびフランジ18の長手方向スリーブ32と協働し、非常時軸受を形成する。
【選択図】 図2
Description
2 ファンシャフト
3 ブレード
4 軸
5 コンプレッサシャフト
6、46 第1の軸受
7、47 第2の軸受
8、14、414 内側リング
9、15、415 外側リング
10 玉軸受
11、19 軸受支持片
13、22 せん断ネジ
13’ 弱化部
14’、20’、20”、26’、28’ 切欠き
14”、26”、28” 歯
14a チャネル
16、416 ローラ
17 リテーナ
18 構造フランジ
20 ハウジング
21、421 固定クランプ
23、436 外表面
24、437 内表面
25 上流側突出環状部
26 下流側突出環状部
27 環状溝
28、428 保持ディスク
29 移動捕捉装置
30 ラビリンスジョイント
31 固定ナット
32、432 長手方向スリーブ
33、433 停止ディスク
34、35 支持面
41 ターボジェットエンジン
45 駆動シャフト
411 支持片
418 フランジ
434 上流側面
435 下流側面
Claims (4)
- 固定構造体と、第1の軸受(6)および第2の軸受(7)に支持される駆動シャフト(5)と一体化されたファンロータ(2)とを備えるターボジェットエンジンであって、ターボジェットエンジンが、手段(28)を備え、該手段(28)が、ファンロータ(2)の軸方向保持手段を形成しかつ/または非常時軸受を形成し、固定構造体の手段(32、33)と協働し、かつ駆動シャフト(5)と一体的に搭載されることを特徴とする、ターボジェットエンジン。
- 第2の軸受(7)が固定される構造フランジ(18)を備え、ファン(2)の軸方向保持手段を形成しかつ/または非常時軸受を形成する手段が、保持ディスク(28)を備え、該保持ディスク(28)が、駆動シャフト(5)に搭載され、ファン(2)を軸方向に保持するためのフランジ(18)の停止ディスク(33)およびフランジ(18)の長手方向スリーブ(32)と協働し、非常時軸受を形成する、請求項1に記載のターボジェットエンジン。
- ファン(2)の軸方向保持手段を形成しかつ/または非常時軸受を形成する手段が、駆動シャフト(5)に直接軸方向応力を伝達するように構成される、請求項1または2に記載のターボジェットエンジン。
- 第2の軸受が、内側リング(14)と、外側リング(15)と、前記内側および外側リング(14、15)の間に搭載されるローラ(16)とを備え、保持ディスク(28)が、駆動シャフト(5)の歯(26”)を軸方向に支持し、かつ第2の軸受(7)の内側リング(14)の長手方向歯(14”)により回転が固定される径方向の歯(28”)を備える、請求項3に記載のターボジェットエンジン。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0401145A FR2866068B1 (fr) | 2004-02-06 | 2004-02-06 | Turboreacteur a soufflante solidaire d'un arbre d'entrainement supporte par un premier et un deuxieme paliers |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005220906A true JP2005220906A (ja) | 2005-08-18 |
JP4617166B2 JP4617166B2 (ja) | 2011-01-19 |
Family
ID=34684993
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005017774A Active JP4617166B2 (ja) | 2004-02-06 | 2005-01-26 | 第1および第2の軸受に支持される駆動シャフトと一体化したファンを有するターボジェットエンジン |
Country Status (11)
Country | Link |
---|---|
US (1) | US7322180B2 (ja) |
EP (1) | EP1564352B1 (ja) |
JP (1) | JP4617166B2 (ja) |
CN (1) | CN100559021C (ja) |
BR (1) | BRPI0500271B1 (ja) |
CA (1) | CA2495982C (ja) |
DE (1) | DE602005018697D1 (ja) |
ES (1) | ES2335778T3 (ja) |
FR (1) | FR2866068B1 (ja) |
RU (1) | RU2386050C2 (ja) |
UA (1) | UA87965C2 (ja) |
Cited By (1)
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JP2008106939A (ja) * | 2006-10-26 | 2008-05-08 | Snecma | 回転シャフト用の軸受機構およびこのような軸受機構を備えるタービンエンジン |
Families Citing this family (29)
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US8499462B2 (en) * | 2006-04-10 | 2013-08-06 | The Gillette Company | Cutting members for shaving razors |
FR2915511B1 (fr) * | 2007-04-27 | 2012-06-08 | Snecma | Limitation de survitesse du rotor d'une turbine de turbomachine |
FR2925123A1 (fr) * | 2007-12-14 | 2009-06-19 | Snecma Sa | Etancheite de fixation de support de palier dans une turbomachine |
US20100047077A1 (en) * | 2007-12-28 | 2010-02-25 | General Electric Company | Ferry Flight Engine Fairing Kit |
US20100043228A1 (en) * | 2007-12-28 | 2010-02-25 | James Lloyd Daniels | Method of Preparing an Engine for Ferry Flight |
FR2929358B1 (fr) * | 2008-03-25 | 2010-08-13 | Snecma | Palier de guidage d'arbre dans une turbomachine |
US8118544B2 (en) * | 2009-01-07 | 2012-02-21 | Honeywell International Inc. | Bearing and retention mechanisms |
US8667775B1 (en) * | 2009-08-05 | 2014-03-11 | The Boeing Company | Reverse flow engine core having a ducted fan with integrated secondary flow blades |
TWI384132B (zh) * | 2009-08-26 | 2013-02-01 | Sunonwealth Electr Mach Ind Co | 散熱風扇構造 |
FR2960026B1 (fr) * | 2010-05-11 | 2014-05-16 | Snecma | Turboreacteur a montage frangible et moyen de retenue axiale de la soufflante |
US8845277B2 (en) | 2010-05-24 | 2014-09-30 | United Technologies Corporation | Geared turbofan engine with integral gear and bearing supports |
US8573922B2 (en) * | 2010-06-15 | 2013-11-05 | Rolls-Royce Corporation | Bearing support |
FR2965298B1 (fr) * | 2010-09-28 | 2012-09-28 | Snecma | Moteur a turbine a gaz comprenant des moyens de retention axiale d'une soufflante dudit moteur |
FR2966208B1 (fr) * | 2010-10-13 | 2012-12-28 | Snecma | Boitier de liaison entre un arbre d'entrainement de soufflante de moteur et un palier de roulement |
CA2760454C (en) | 2010-12-03 | 2019-02-19 | Pratt & Whitney Canada Corp. | Gas turbine rotor containment |
RU2459966C1 (ru) * | 2011-04-06 | 2012-08-27 | Открытое акционерное общество "Авиадвигатель" | Опора газотурбинного двигателя |
GB2494178B (en) | 2011-09-02 | 2013-07-31 | Rolls Royce Plc | A catcher ring assembly |
US9115598B2 (en) | 2012-06-05 | 2015-08-25 | United Technologies Corporation | Front bearing support for a fan drive gear system |
FR2999237B1 (fr) | 2012-12-11 | 2018-07-13 | Safran Aircraft Engines | Guidage d'arbres de turbomachine |
FR3005098B1 (fr) * | 2013-04-30 | 2015-05-15 | Snecma | Support de palier d'une turbomachine comportant une ouverture d'acces pour l'assemblage de servitudes |
FR3016189B1 (fr) * | 2014-01-07 | 2018-09-28 | Safran Aircraft Engines | Dispositif de reduction epicycloidal pour l'entrainement en rotation des ensembles de pales d'une turbomachine a reducteur |
SE537987C2 (sv) * | 2014-04-07 | 2016-01-12 | Cgrain Ab | Avbildningssystem för granulärt material med homogen bakgrund |
FR3026774B1 (fr) * | 2014-10-07 | 2020-07-17 | Safran Aircraft Engines | Turbomachine comportant un dispositif de freinage du rotor de soufflante. |
GB201704984D0 (en) | 2017-03-29 | 2017-05-10 | Rolls Royce Plc | Mitigation of effects of fan blade off in a gas turbine engine |
FR3071546B1 (fr) | 2017-09-25 | 2019-09-13 | Safran Aircraft Engines | Retention axiale de l'arbre de soufflante dans un moteur a turbine a gaz |
JP7032279B2 (ja) * | 2018-10-04 | 2022-03-08 | 本田技研工業株式会社 | ガスタービンエンジン |
FR3096744B1 (fr) * | 2019-06-03 | 2022-01-14 | Safran Aircraft Engines | Ensemble de support et de guidage d’un arbre d’entrainement de turbomachine d’aeronef |
FR3107089B1 (fr) | 2020-02-07 | 2023-03-10 | Safran Aircraft Engines | Retenue axiale d’une soufflante dans un turboréacteur |
US11408304B2 (en) * | 2020-10-08 | 2022-08-09 | Pratt & Whitney Canada Corp. | Gas turbine engine bearing housing |
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JPS5642721A (en) * | 1979-08-23 | 1981-04-21 | Gen Electric | Supporting device of shaft |
US5029439A (en) * | 1988-12-15 | 1991-07-09 | Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas turbine engine including a turbine braking device |
US6009701A (en) * | 1996-12-20 | 2000-01-04 | Rolls-Royce, Plc | Ducted fan gas turbine engine having a frangible connection |
JP2000192953A (ja) * | 1998-12-23 | 2000-07-11 | United Technol Corp <Utc> | 軸受システム |
US6098399A (en) * | 1997-02-15 | 2000-08-08 | Rolls-Royce Plc | Ducted fan gas turbine engine |
US20030142894A1 (en) * | 2002-01-26 | 2003-07-31 | Bernhard Woehrl | Rotary bearing assembly having a preset breaking point |
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FR2866073B1 (fr) * | 2004-02-11 | 2006-07-28 | Snecma Moteurs | Turboreacteur ayant deux soufflantes contrarotatives solidaires d'un compresseur a basse pression contrarotatif |
FR2871517B1 (fr) * | 2004-06-11 | 2006-09-01 | Snecma Moteurs Sa | Turbomachine avec moyens de retenue axiale du rotor |
FR2874238B1 (fr) * | 2004-08-12 | 2006-12-01 | Snecma Moteurs Sa | Turbomachine a soufflantes contrarotatives |
-
2004
- 2004-02-06 FR FR0401145A patent/FR2866068B1/fr not_active Expired - Fee Related
- 2004-12-29 US US11/023,601 patent/US7322180B2/en active Active
-
2005
- 2005-01-19 BR BRPI0500271-0A patent/BRPI0500271B1/pt active IP Right Grant
- 2005-01-26 JP JP2005017774A patent/JP4617166B2/ja active Active
- 2005-01-28 DE DE602005018697T patent/DE602005018697D1/de active Active
- 2005-01-28 ES ES05300073T patent/ES2335778T3/es active Active
- 2005-01-28 EP EP05300073A patent/EP1564352B1/fr active Active
- 2005-02-01 UA UAA200500916A patent/UA87965C2/ru unknown
- 2005-02-02 CA CA2495982A patent/CA2495982C/fr active Active
- 2005-02-03 CN CNB2005100080350A patent/CN100559021C/zh active Active
- 2005-02-04 RU RU2005102780/06A patent/RU2386050C2/ru active
Patent Citations (6)
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JPS5642721A (en) * | 1979-08-23 | 1981-04-21 | Gen Electric | Supporting device of shaft |
US5029439A (en) * | 1988-12-15 | 1991-07-09 | Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas turbine engine including a turbine braking device |
US6009701A (en) * | 1996-12-20 | 2000-01-04 | Rolls-Royce, Plc | Ducted fan gas turbine engine having a frangible connection |
US6098399A (en) * | 1997-02-15 | 2000-08-08 | Rolls-Royce Plc | Ducted fan gas turbine engine |
JP2000192953A (ja) * | 1998-12-23 | 2000-07-11 | United Technol Corp <Utc> | 軸受システム |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008106939A (ja) * | 2006-10-26 | 2008-05-08 | Snecma | 回転シャフト用の軸受機構およびこのような軸受機構を備えるタービンエンジン |
JP4611358B2 (ja) * | 2006-10-26 | 2011-01-12 | スネクマ | 回転シャフト用の軸受機構およびこのような軸受機構を備えるタービンエンジン |
Also Published As
Publication number | Publication date |
---|---|
CA2495982C (fr) | 2011-11-08 |
UA87965C2 (ru) | 2009-09-10 |
EP1564352A3 (fr) | 2005-08-31 |
RU2005102780A (ru) | 2006-07-10 |
US7322180B2 (en) | 2008-01-29 |
US20050172608A1 (en) | 2005-08-11 |
EP1564352B1 (fr) | 2010-01-06 |
RU2386050C2 (ru) | 2010-04-10 |
FR2866068B1 (fr) | 2006-07-07 |
BRPI0500271B1 (pt) | 2015-06-23 |
ES2335778T3 (es) | 2010-04-05 |
CN100559021C (zh) | 2009-11-11 |
JP4617166B2 (ja) | 2011-01-19 |
CN1670347A (zh) | 2005-09-21 |
FR2866068A1 (fr) | 2005-08-12 |
CA2495982A1 (fr) | 2005-08-06 |
DE602005018697D1 (de) | 2010-02-25 |
BRPI0500271A (pt) | 2005-09-27 |
EP1564352A2 (fr) | 2005-08-17 |
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Free format text: JAPANESE INTERMEDIATE CODE: R250 |
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R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
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R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |