JP4237712B2 - 高いバイパス比を有するスリースプールバイパスターボジェット - Google Patents
高いバイパス比を有するスリースプールバイパスターボジェット Download PDFInfo
- Publication number
- JP4237712B2 JP4237712B2 JP2005026018A JP2005026018A JP4237712B2 JP 4237712 B2 JP4237712 B2 JP 4237712B2 JP 2005026018 A JP2005026018 A JP 2005026018A JP 2005026018 A JP2005026018 A JP 2005026018A JP 4237712 B2 JP4237712 B2 JP 4237712B2
- Authority
- JP
- Japan
- Prior art keywords
- fan
- grid
- bypass
- turbojet
- air flow
- 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
- 230000002441 reversible effect Effects 0.000 claims 1
- 238000002955 isolation Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
・ それぞれ可動径方向アームは、グリッドキャリアリングに埋め込まれた径方向内側ヒンジを有している。
・ それぞれ可動径方向アームは、ファンケーシングに埋め込まれた径方向外側ヒンジを有している。
3 フロントファン
4 内側駆動シャフト
5 リアファン
6 中間駆動シャフト
7 低圧圧縮機
8、13 チャネル
10、14 ブレード
11、15、41 ホイール
12 ファンケーシング
16、17、42 コーン
18 シャフト間当接部
19 シャフト間ローラベアリング
20、22 スラストベアリング
21 ローラベアリング
24 高圧圧縮機
23 駆動シャフト
30、48 外側構造グリッド
31 内側構造グリッド
32 環状ボックス
33 隔離先端
40 ロータブレード
45、46 ステータ翼
43 シェル
47 グリッドキャリアリング
49 アーム
50 可変ピッチステータ
51 可動径方向アーム
52 径方向内側ヒンジ
53 径方向外側ヒンジ
54 駆動アーム
55 自由端
56 制御リング
Claims (6)
- 高バイパス比を有するスリースプールバイパスターボジェットであって、ターボジェットが、中間ケーシング(2)の前方にフロントファン(3)およびリアファン(5)を有し、前記中間ケーシング(2)が、バイパス空気流(F2)に外側構造グリッド(30)を呈し、かつ主空気流(F1)に内側構造グリッド(31)を呈し、フロントファンおよびリアファンが、バイパス空気流(F2)の外側を画定するファンケーシング(12)まで径方向外側へ延びるブレード(10、14)を有し、ターボジェットが、主空気流(F1)のためのチャネル(8)に入る空気を圧縮するための低圧圧縮機(7)をさらに有しており、前記フロントファン(3)および前記リアファン(5)が、同軸である2つのシャフト(4、6)によって直接かつ別々に回転され、
低圧圧縮機(7)が、フロントファン(3)のブレード(10)とリアファン(5)のブレード(14)との間で軸方向に配置されているとともに、フロントファン(3)のための駆動シャフト(4)によって駆動されるホイール(41)の周縁から延びるロータブレード(40)の少なくとも1つのリングと、ロータブレード(40)の前記リングの両側に軸方向に配置され、かつグリッドキャリアリング(47)の径方向内側に配置されたステータ翼(45、46)の少なくとも2つのグリッドとを含み、前記グリッドキャリアリング(47)が、バイパス空気流(F2)に配置された外側グリッド(48)によって支持され、前記外側グリッドが、ファンケーシング(12)によって支持されていることと、可変ピッチステータ(50)が、前記外側グリッド(48)よりも下流側に配置されていることとを特徴とする、バイパスターボジェット。 - 外側グリッド(48)が、複数の固定径方向アーム(49)を有し、可変ピッチステータ(50)が、径方向軸の周りに旋回することのできる複数の可動径方向アーム(51)を有し、それぞれ可動径方向アーム(51)が、固定径方向アーム(49)のすぐ後方に配置されていることを特徴とする、請求項1に記載のターボジェット。
- それぞれ可動径方向アーム(51)が、グリッドキャリアリング(47)に埋め込まれた径方向内側ヒンジ(52)を有していることを特徴とする、請求項2に記載のターボジェット。
- それぞれ可動径方向アーム(51)が、ファンケーシング(12)に埋め込まれた径方向外側ヒンジ(53)を有していることを特徴とする、請求項3に記載のターボジェット。
- 径方向外側ヒンジ(53)には、制御リング(56)にヒンジ留めされた自由端(55)を有する駆動アーム(54)が取り付けられていることを特徴とする、請求項4に記載のターボジェット。
- フロントファン(3)およびリアファン(5)が、二重反転可能なファンであることを特徴とする、請求項1に記載のターボジェット。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0401384A FR2866387B1 (fr) | 2004-02-12 | 2004-02-12 | Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005226644A JP2005226644A (ja) | 2005-08-25 |
JP4237712B2 true JP4237712B2 (ja) | 2009-03-11 |
Family
ID=34707994
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005026018A Active JP4237712B2 (ja) | 2004-02-12 | 2005-02-02 | 高いバイパス比を有するスリースプールバイパスターボジェット |
Country Status (10)
Country | Link |
---|---|
US (1) | US7299621B2 (ja) |
EP (1) | EP1566522B1 (ja) |
JP (1) | JP4237712B2 (ja) |
CN (1) | CN1654804B (ja) |
CA (1) | CA2495992C (ja) |
DE (1) | DE602005010923D1 (ja) |
ES (1) | ES2317168T3 (ja) |
FR (1) | FR2866387B1 (ja) |
RU (1) | RU2364740C2 (ja) |
UA (1) | UA83995C2 (ja) |
Families Citing this family (54)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0314123D0 (en) * | 2003-06-18 | 2003-07-23 | Rolls Royce Plc | A gas turbine engine |
DE102004042739A1 (de) * | 2004-09-03 | 2006-03-09 | Mtu Aero Engines Gmbh | Fan für ein Flugtriebwerk sowie Flugtriebwerk |
US7882694B2 (en) * | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
FR2889863B1 (fr) * | 2005-08-22 | 2007-11-02 | Snecma | Compresseur comportant une pluralite de caissons reconstituant un volume annulaire de separation de flux dans une turbomachine. |
US7490461B2 (en) * | 2005-10-19 | 2009-02-17 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7685808B2 (en) * | 2005-10-19 | 2010-03-30 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7841165B2 (en) * | 2006-10-31 | 2010-11-30 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US8104265B2 (en) * | 2007-06-28 | 2012-01-31 | United Technologies Corporation | Gas turbines with multiple gas flow paths |
US8161728B2 (en) * | 2007-06-28 | 2012-04-24 | United Technologies Corp. | Gas turbines with multiple gas flow paths |
US9359960B2 (en) * | 2007-06-28 | 2016-06-07 | United Technologies Corporation | Gas turbines with multiple gas flow paths |
US20120222398A1 (en) * | 2007-07-27 | 2012-09-06 | Smith Peter G | Gas turbine engine with geared architecture |
FR2921973B1 (fr) * | 2007-10-04 | 2011-04-29 | Snecma | Carter intermediaire de turboreacteur et turboreacteur |
EP2123884B1 (en) * | 2008-05-13 | 2015-03-04 | Rolls-Royce Corporation | Dual clutch arrangement |
US8128021B2 (en) | 2008-06-02 | 2012-03-06 | United Technologies Corporation | Engine mount system for a turbofan gas turbine engine |
US20140174056A1 (en) | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
US8887485B2 (en) * | 2008-10-20 | 2014-11-18 | Rolls-Royce North American Technologies, Inc. | Three spool gas turbine engine having a clutch and compressor bypass |
FR2942273B1 (fr) * | 2009-02-18 | 2011-06-10 | Snecma | Moteur double flux a roues de turbine contrarotatives |
GB0910955D0 (en) | 2009-06-25 | 2009-08-05 | Rolls Royce Plc | Adjustable camber aerofoil |
US8176725B2 (en) * | 2009-09-09 | 2012-05-15 | United Technologies Corporation | Reversed-flow core for a turbofan with a fan drive gear system |
US9631558B2 (en) | 2012-01-03 | 2017-04-25 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
US9239012B2 (en) | 2011-06-08 | 2016-01-19 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
FR2977635B1 (fr) * | 2011-07-04 | 2017-03-24 | Snecma | Dispositif d'arbre d'entrainement d'une turbomachine |
US9506402B2 (en) | 2011-07-29 | 2016-11-29 | United Technologies Corporation | Three spool engine bearing configuration |
CA2853694C (en) * | 2012-01-09 | 2016-03-22 | United Technologies Corporation | Gas turbine engine with geared architecture |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US10036351B2 (en) | 2012-04-02 | 2018-07-31 | United Technologies Corporation | Geared turbofan with three co-rotating turbines |
US10018119B2 (en) * | 2012-04-02 | 2018-07-10 | United Technologies Corporation | Geared architecture with inducer for gas turbine engine |
US9074485B2 (en) | 2012-04-25 | 2015-07-07 | United Technologies Corporation | Geared turbofan with three turbines all counter-rotating |
US10036350B2 (en) | 2012-04-30 | 2018-07-31 | United Technologies Corporation | Geared turbofan with three turbines all co-rotating |
US20150308351A1 (en) | 2012-05-31 | 2015-10-29 | United Technologies Corporation | Fundamental gear system architecture |
US8756908B2 (en) | 2012-05-31 | 2014-06-24 | United Technologies Corporation | Fundamental gear system architecture |
US8572943B1 (en) | 2012-05-31 | 2013-11-05 | United Technologies Corporation | Fundamental gear system architecture |
FR2994452B1 (fr) * | 2012-08-09 | 2016-12-23 | Snecma | Turbomachine comportant une pluralite d'aubes radiales fixes montees en amont de la soufflante |
CN103867337B (zh) * | 2012-12-11 | 2016-02-03 | 中航商用航空发动机有限责任公司 | 大涵道比变循环发动机 |
WO2014133645A2 (en) * | 2013-02-20 | 2014-09-04 | Rolls-Royce North American Technologies Inc. | Gas turbine engine having configurable bypass passage |
FR3003303B1 (fr) * | 2013-03-15 | 2017-06-30 | Snecma | Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion |
EP3004595B1 (en) * | 2013-06-03 | 2020-09-02 | United Technologies Corporation | Turbofan engine bearing and gearbox arrangement |
US9777642B2 (en) | 2014-11-21 | 2017-10-03 | General Electric Company | Gas turbine engine and method of assembling the same |
US10077660B2 (en) | 2014-12-03 | 2018-09-18 | General Electric Company | Turbine engine assembly and method of manufacturing |
CN104500269B (zh) * | 2014-12-11 | 2016-04-20 | 南京航空航天大学 | 带内环空气涡轮的自驱动风扇大涵道比涡扇发动机 |
US10669946B2 (en) | 2015-06-05 | 2020-06-02 | Raytheon Technologies Corporation | Geared architecture for a gas turbine engine |
FR3039227B1 (fr) * | 2015-07-22 | 2019-12-27 | Safran Aircraft Engines | Aeronef comprenant un propulseur arriere carene avec stator d’entree a volets mobiles |
US20170058831A1 (en) * | 2015-08-27 | 2017-03-02 | William Barry Bryan | Gas turbine engine having radially-split inlet guide vanes |
US11391298B2 (en) | 2015-10-07 | 2022-07-19 | General Electric Company | Engine having variable pitch outlet guide vanes |
FR3043714B1 (fr) * | 2015-11-16 | 2017-12-22 | Snecma | Partie avant de turbomachine d'aeronef comprenant une soufflante unique entrainee par un reducteur, ainsi que des aubes directrices de sortie structurales agencees en partie en amont d'un bec de separation |
US10563593B2 (en) * | 2016-01-04 | 2020-02-18 | Rolls-Royce North American Technologies, Inc. | System and method of transferring power in a gas turbine engine |
US20170218842A1 (en) * | 2016-02-02 | 2017-08-03 | General Electric Company | Adjusting Airflow Distortion in Gas Turbine Engine |
US10794281B2 (en) | 2016-02-02 | 2020-10-06 | General Electric Company | Gas turbine engine having instrumented airflow path components |
US11073090B2 (en) | 2016-03-30 | 2021-07-27 | General Electric Company | Valved airflow passage assembly for adjusting airflow distortion in gas turbine engine |
US10753278B2 (en) | 2016-03-30 | 2020-08-25 | General Electric Company | Translating inlet for adjusting airflow distortion in gas turbine engine |
BE1025299B9 (fr) * | 2017-06-09 | 2020-05-04 | Safran Aero Boosters Sa | Compresseur a geometrie variable de turbomachine axiale |
US10961921B2 (en) | 2018-09-19 | 2021-03-30 | Pratt & Whitney Canada Corp. | Model-based control system and method for a turboprop engine |
FR3118094A1 (fr) * | 2020-12-23 | 2022-06-24 | Safran | Aube de stator avec portion mobile, module de turbomachine equipe d’une telle aube de stator et turbomachine correspondante |
WO2024121464A1 (fr) * | 2022-12-05 | 2024-06-13 | Safran Aircraft Engines | Turbomachine d'aéronef a triple flux |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1305302A (ja) * | 1970-04-28 | 1973-01-31 | ||
US4791783A (en) * | 1981-11-27 | 1988-12-20 | General Electric Company | Convertible aircraft engine |
FR2560642A1 (fr) * | 1984-03-02 | 1985-09-06 | Gen Electric | Moteur a turbosoufflante a contre-rotation |
GB2194292A (en) * | 1986-08-29 | 1988-03-02 | Gen Electric | High bypass ratio counterrotating turbofan engine |
US4860537A (en) * | 1986-08-29 | 1989-08-29 | Brandt, Inc. | High bypass ratio counterrotating gearless front fan engine |
GB8630754D0 (en) * | 1986-12-23 | 1987-02-04 | Rolls Royce Plc | Turbofan gas turbine engine |
US5160251A (en) * | 1991-05-13 | 1992-11-03 | General Electric Company | Lightweight engine turbine bearing support assembly for withstanding radial and axial loads |
US5388964A (en) * | 1993-09-14 | 1995-02-14 | General Electric Company | Hybrid rotor blade |
US5806303A (en) * | 1996-03-29 | 1998-09-15 | General Electric Company | Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle |
US6732502B2 (en) * | 2002-03-01 | 2004-05-11 | General Electric Company | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
-
2004
- 2004-02-12 FR FR0401384A patent/FR2866387B1/fr not_active Expired - Fee Related
-
2005
- 2005-01-27 EP EP05290180A patent/EP1566522B1/fr active Active
- 2005-01-27 DE DE602005010923T patent/DE602005010923D1/de active Active
- 2005-01-27 ES ES05290180T patent/ES2317168T3/es active Active
- 2005-01-31 US US11/045,365 patent/US7299621B2/en active Active
- 2005-02-02 JP JP2005026018A patent/JP4237712B2/ja active Active
- 2005-02-02 CA CA2495992A patent/CA2495992C/fr active Active
- 2005-02-10 UA UAA200501217A patent/UA83995C2/ru unknown
- 2005-02-11 RU RU2005103706/06A patent/RU2364740C2/ru active
- 2005-02-16 CN CN2005100091798A patent/CN1654804B/zh active Active
Also Published As
Publication number | Publication date |
---|---|
RU2364740C2 (ru) | 2009-08-20 |
US20050241291A1 (en) | 2005-11-03 |
CN1654804A (zh) | 2005-08-17 |
RU2005103706A (ru) | 2006-07-20 |
UA83995C2 (ru) | 2008-09-10 |
CA2495992C (fr) | 2011-11-22 |
CN1654804B (zh) | 2011-06-01 |
FR2866387B1 (fr) | 2008-03-14 |
DE602005010923D1 (de) | 2008-12-24 |
ES2317168T3 (es) | 2009-04-16 |
EP1566522A1 (fr) | 2005-08-24 |
FR2866387A1 (fr) | 2005-08-19 |
US7299621B2 (en) | 2007-11-27 |
JP2005226644A (ja) | 2005-08-25 |
CA2495992A1 (fr) | 2005-08-12 |
EP1566522B1 (fr) | 2008-11-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4237712B2 (ja) | 高いバイパス比を有するスリースプールバイパスターボジェット | |
JP5662629B2 (ja) | ターボファンエンジンアセンブリ | |
US7412819B2 (en) | Turbojet architecture with two fans at the front | |
JP5155648B2 (ja) | ターボファンエンジンアセンブリ | |
EP1921290B1 (en) | Turbofan engine assembly | |
RU2468233C2 (ru) | Узел газотурбинного двигателя | |
JP5080777B2 (ja) | 二重反転ファン組立体及びそれを含むガスタービンエンジン組立体 | |
JP4906465B2 (ja) | ガスタービンエンジン組立体及びそれを組み立てる方法 | |
CA2606860C (en) | Turbofan engine assembly and method of assembling same | |
JP5019721B2 (ja) | ガスタービンエンジンを組立てるための方法及び装置 | |
CN1952368B (zh) | 燃气轮机装置及其装配方法 | |
US7905083B2 (en) | Turbofan engine assembly and method of assembling same | |
JP5111823B2 (ja) | ガスタービンエンジン組立体及びそれを組み立てる方法 | |
US7290386B2 (en) | Counter-rotating gas turbine engine and method of assembling same | |
US10823064B2 (en) | Gas turbine engine | |
CN1952366A (zh) | 燃气轮机装置及其装配方法 | |
JPS61275550A (ja) | 航空機用ガスタ−ビンエンジン | |
CA2612031A1 (en) | Turbofan engine assembly and method of assembling same | |
JP2005226642A (ja) | 二重反転可能な低圧圧縮機に固定された2つの二重反転可能なファンを有するターボジェット |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20060413 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20080801 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20080805 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20081105 |
|
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: 20081202 |
|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20081218 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 4237712 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20111226 Year of fee payment: 3 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20121226 Year of fee payment: 4 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20131226 Year of fee payment: 5 |
|
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 |
|
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 |