JP4646644B2 - 前部に二つのファンを有するターボジェット構造 - Google Patents
前部に二つのファンを有するターボジェット構造 Download PDFInfo
- Publication number
- JP4646644B2 JP4646644B2 JP2005024707A JP2005024707A JP4646644B2 JP 4646644 B2 JP4646644 B2 JP 4646644B2 JP 2005024707 A JP2005024707 A JP 2005024707A JP 2005024707 A JP2005024707 A JP 2005024707A JP 4646644 B2 JP4646644 B2 JP 4646644B2
- Authority
- JP
- Japan
- Prior art keywords
- fan
- bearing
- turbojet
- drive shaft
- intermediate casing
- 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
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000012634 fragment Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
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
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
- F04D29/0563—Bearings cartridges
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
-
- 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
- F02K3/065—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 front and aft fans
-
- 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
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
- F04D29/059—Roller bearings
-
- 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
-
- 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
2 中間ケーシング
3 前部ファン
4、73 駆動シャフト
5 後部ファン
6 回転シャフト
7 低圧圧縮機
8、13 チャネル
10、14 ブレード
11、15、42 ホイール
12 ファンケーシング
16、17 コーン
18 下流側リング
19、41 ロータブレード
30 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 スラストテークアップバー
40 ロータブレードのリング
43 ブシュ
44 中間リング
45、46 リング
47、48 ステータブレードのグリッド
49 外側ステータ
50 分離先端部
60 第2の中間ケーシング
61 第2の外側構造グリッド
62 第2の内側構造グリッド
63 環状ボックス
70、72、81 スラスト軸受け
71 ローラ軸受け
74 高圧圧縮機
80 シャフト間軸受け
Claims (6)
- 高バイパス比を有する3スプールバイパスターボジェットであって、該ターボジェットが、第1の中間ケーシング(2)の前部に前部ファン(3)および後部ファン(5)を有し、前記第1の中間ケーシング(2)が、バイパス空気流(F2)に外側構造グリッド(30)を与え、かつ主空気流(F1)に内側構造グリッド(31)を与え、前部および後部ファンが、バイパス空気流(F2)を外側に画定するファンケーシング(12)にまで外向きに径方向に延びるブレード(10、14)を有し、前記ターボジェットが、主空気流(F1)のためのチャネル(8)内に流入する空気を圧縮するための低圧圧縮機(7)をさらに有し、前記前部ファン(3)および後部ファン(5)が、互いに同軸である二つのシャフト(4、6)によって別々に直接回転される、高バイパス比を有する3スプールバイパスターボジェットであり、
後部ファン(5)のブレード(14)が、ホイール(15)からバイパス空気流(F2)に延び、前記ホイール(15)が、低圧圧縮機(7)においてロータブレード(19)の下流側リング(18)を介して、駆動シャフト(6)に接続され、前記低圧圧縮機は、前部ファン(3)のための駆動シャフト(4)によって駆動されるロータブレード(41)の少なくとも一つの上流側リングと、ステータブレードのグリッド(47、48)が延びる内腔内の外側ステータ(49)とをさらに備えており、前記グリッドが、ロータブレードのリング(41、44、19)間に交互配置され、前記外側ステータが、前部ファン(3)のブレード(10)と後部ファン(5)のブレード(14)との間のバイパス空気流(F2)内の第2の外側構造グリッド(61)と、主空気流(F1)内の第2の内側構造グリッド(62)とを有する第2の中間ケーシング(60)を介して、ファンケーシング(12)によって保持されていることと、第1の中間ケーシング(2)が、軸方向スラスト軸受け(70)を介して後部ファン(5)の駆動シャフト(6)を支持し、かつシャフト間軸受け(80)を介して前部ファンの駆動シャフト(4)を支持し、また一方の追加の軸受け(71)が、第2の中間ケーシング(60)と後部ファン(5)の駆動シャフト(6)との間に挿入され、他方の追加の軸受け(81)が、第2の中間ケーシング(60)と前部ファン(3)の駆動シャフト(4)との間に挿入されることとを特徴とする、3スプールバイパスターボジェット。 - 第2の中間ケーシング(60)とシャフト間軸受け(80)とによって支持される、前部ファン(3)の駆動シャフト(4)のスラスト軸受け(81)が、ローラ軸受け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。
- シャフト間軸受け(80)が、スラスト軸受けであり、第2の中間ケーシング(60)と前部ファン(3)の駆動シャフト(4)との間に挿入された軸受け(81)が、ローラ軸受け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。
- 第2の中間ケーシング(60)と前部ファン(3)の駆動シャフト(4)との間に挿入された軸受け(71)が、ローラ軸受けであることを特徴とする、請求項2または3のいずれか一項に記載のターボジェット。
- 第1の中間ケーシング(2)が、スラスト軸受け(72)を介して高圧圧縮機(74)の駆動シャフト(73)をさらに支持することを特徴とする、請求項1から4のいずれか一項に記載のターボジェット。
- 前部ファン(3)および後部ファン(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から4のいずれか一項に記載のターボジェット。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0401336A FR2866074B1 (fr) | 2004-02-11 | 2004-02-11 | Architecture d'un turboreacteur ayant une double soufflante a l'avant |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005226643A JP2005226643A (ja) | 2005-08-25 |
JP4646644B2 true JP4646644B2 (ja) | 2011-03-09 |
Family
ID=34685006
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005024707A Active JP4646644B2 (ja) | 2004-02-11 | 2005-02-01 | 前部に二つのファンを有するターボジェット構造 |
Country Status (10)
Country | Link |
---|---|
US (1) | US7412819B2 (ja) |
EP (1) | EP1564397B1 (ja) |
JP (1) | JP4646644B2 (ja) |
CN (1) | CN100470041C (ja) |
CA (1) | CA2495594C (ja) |
DE (1) | DE602005000116T2 (ja) |
ES (1) | ES2271935T3 (ja) |
FR (1) | FR2866074B1 (ja) |
RU (1) | RU2357092C2 (ja) |
UA (1) | UA83346C2 (ja) |
Families Citing this family (43)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005018139A1 (de) * | 2005-04-20 | 2006-10-26 | Mtu Aero Engines Gmbh | Stahltriebwerk |
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. |
US7513103B2 (en) * | 2005-10-19 | 2009-04-07 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7921634B2 (en) * | 2006-10-31 | 2011-04-12 | General Electric Company | Turbofan engine assembly and method of assembling same |
US7841165B2 (en) * | 2006-10-31 | 2010-11-30 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7882693B2 (en) * | 2006-11-29 | 2011-02-08 | General Electric Company | Turbofan engine assembly and method of assembling same |
FR2918120B1 (fr) | 2007-06-28 | 2009-10-02 | Snecma Sa | Turbomachine a double soufflante |
FR2921973B1 (fr) * | 2007-10-04 | 2011-04-29 | Snecma | Carter intermediaire de turboreacteur et turboreacteur |
EP2177735A3 (en) * | 2008-10-20 | 2012-02-15 | Rolls-Royce North American Technologies, Inc. | Turbofan |
FR2942273B1 (fr) * | 2009-02-18 | 2011-06-10 | Snecma | Moteur double flux a roues de turbine contrarotatives |
GB0911100D0 (en) * | 2009-06-29 | 2009-08-12 | Rolls Royce Plc | Propulsive fan system |
US9784181B2 (en) * | 2009-11-20 | 2017-10-10 | United Technologies Corporation | Gas turbine engine architecture with low pressure compressor hub between high and low rotor thrust bearings |
US8777793B2 (en) | 2011-04-27 | 2014-07-15 | United Technologies Corporation | Fan drive planetary gear system integrated carrier and torque frame |
FR2976316B1 (fr) * | 2011-06-08 | 2013-06-14 | Snecma | Turbomachine comportant un palier flottant de guidage d'un arbre de turbomachine |
US9279388B2 (en) | 2011-11-01 | 2016-03-08 | United Technologies Corporation | Gas turbine engine with two-spool fan and variable vane turbine |
BR102012027097B1 (pt) * | 2011-11-23 | 2022-01-04 | United Technologies Corporation | Motor de turbina a gás |
US10145266B2 (en) * | 2012-01-31 | 2018-12-04 | United Technologies Corporation | Gas turbine engine shaft bearing arrangement |
US9038366B2 (en) | 2012-01-31 | 2015-05-26 | United Technologies Corporation | LPC flowpath shape with gas turbine engine shaft bearing configuration |
US10400629B2 (en) | 2012-01-31 | 2019-09-03 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
US8863491B2 (en) | 2012-01-31 | 2014-10-21 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
US9228535B2 (en) * | 2012-07-24 | 2016-01-05 | United Technologies Corporation | Geared fan with inner counter rotating compressor |
US9885282B2 (en) * | 2013-03-15 | 2018-02-06 | United Technologies Corporation | Turbofan engine bearing and gearbox arrangement |
FR3003303B1 (fr) * | 2013-03-15 | 2017-06-30 | Snecma | Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion |
US9732629B2 (en) * | 2013-03-15 | 2017-08-15 | United Technologies Corporation | Turbofan engine main bearing arrangement |
WO2014197155A1 (en) * | 2013-06-03 | 2014-12-11 | United Technologies Corporation | Turbofan engine bearing and gearbox arrangement |
DE102013224081B4 (de) | 2013-11-26 | 2015-11-05 | Man Diesel & Turbo Se | Verdichter |
US10487747B2 (en) * | 2014-04-29 | 2019-11-26 | Safran Aircraft Engines | Modular assembly for a turbine engine |
CN103982302B (zh) * | 2014-05-23 | 2016-02-17 | 中国航空动力机械研究所 | 用于燃气轮机发电机组的冷却机构及燃气轮机发电机组 |
BE1024024B1 (fr) * | 2014-10-09 | 2017-10-30 | Safran Aero Boosters S.A. | Compresseur de turbomachine axiale avec rotor contrarotatif |
BE1022364B1 (fr) * | 2014-10-27 | 2016-03-17 | Techspace Aero S.A. | Compresseur de turbomachine axiale avec double rotors contrarotatifs |
GB201421882D0 (en) * | 2014-12-09 | 2015-01-21 | Rolls Royce Plc | Bearing load sharing system |
FR3046202B1 (fr) * | 2015-12-24 | 2017-12-29 | Snecma | Turboreacteur avec un moyen de reprise de poussee sur le carter inter-compresseurs |
FR3046201B1 (fr) * | 2015-12-24 | 2018-01-19 | Safran Aircraft Engines | Turboreacteur avec un moyen de reprise de poussee sur le carter inter-compresseurs |
US10669947B2 (en) | 2016-07-11 | 2020-06-02 | Raytheon Technologies Corporation | Geared gas turbine engine |
DE102016118779A1 (de) | 2016-10-04 | 2018-04-05 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofan-Triebwerk für ein ziviles Überschallflugzeug |
GB201704502D0 (en) * | 2017-03-22 | 2017-05-03 | Rolls Royce Plc | Gas turbine engine |
US11333076B2 (en) * | 2017-12-21 | 2022-05-17 | Raytheon Technologies Corporation | Power takeoff transmission |
JP7059028B2 (ja) * | 2018-02-01 | 2022-04-25 | 本田技研工業株式会社 | ガスタービンエンジン |
EP3587774A1 (en) * | 2018-06-27 | 2020-01-01 | Rolls-Royce plc | Gas turbine |
FR3086348B1 (fr) * | 2018-09-21 | 2020-12-04 | Safran Aircraft Engines | Turboreacteur a reducteur |
CN109538353B (zh) * | 2018-11-07 | 2021-01-26 | 中国航发湖南动力机械研究所 | 飞行器及其发动机 |
CN114876869A (zh) * | 2021-02-05 | 2022-08-09 | 中国航发商用航空发动机有限责任公司 | 风扇叶片以及航空发动机 |
CN114562387B (zh) * | 2022-03-21 | 2023-05-05 | 西北工业大学 | 一种外置风扇式跨介质发动机 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3486328A (en) * | 1967-01-11 | 1969-12-30 | Snecma | Multiflow turbojet engine |
US3713748A (en) * | 1970-04-28 | 1973-01-30 | Mini Of Aviat Supply | Gas turbine ducted fan engine |
US3861139A (en) * | 1973-02-12 | 1975-01-21 | Gen Electric | Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition |
GB2189844A (en) * | 1986-04-30 | 1987-11-04 | Rolls Royce | Gas turbine engines |
US4860537A (en) * | 1986-08-29 | 1989-08-29 | Brandt, Inc. | High bypass ratio counterrotating gearless front fan engine |
US5272868A (en) * | 1993-04-05 | 1993-12-28 | General Electric Company | Gas turbine engine lubrication system |
US20030163983A1 (en) * | 2002-03-01 | 2003-09-04 | Seda Jorge F. | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
-
2004
- 2004-02-11 FR FR0401336A patent/FR2866074B1/fr not_active Expired - Fee Related
-
2005
- 2005-01-26 US US11/041,998 patent/US7412819B2/en active Active
- 2005-02-01 CA CA2495594A patent/CA2495594C/fr active Active
- 2005-02-01 JP JP2005024707A patent/JP4646644B2/ja active Active
- 2005-02-08 CN CNB2005100094194A patent/CN100470041C/zh active Active
- 2005-02-10 ES ES05290295T patent/ES2271935T3/es active Active
- 2005-02-10 DE DE602005000116T patent/DE602005000116T2/de active Active
- 2005-02-10 RU RU2005103601/06A patent/RU2357092C2/ru active
- 2005-02-10 UA UAA200501216A patent/UA83346C2/uk unknown
- 2005-02-10 EP EP05290295A patent/EP1564397B1/fr active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3486328A (en) * | 1967-01-11 | 1969-12-30 | Snecma | Multiflow turbojet engine |
US3713748A (en) * | 1970-04-28 | 1973-01-30 | Mini Of Aviat Supply | Gas turbine ducted fan engine |
US3861139A (en) * | 1973-02-12 | 1975-01-21 | Gen Electric | Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition |
GB2189844A (en) * | 1986-04-30 | 1987-11-04 | Rolls Royce | Gas turbine engines |
US4860537A (en) * | 1986-08-29 | 1989-08-29 | Brandt, Inc. | High bypass ratio counterrotating gearless front fan engine |
US5272868A (en) * | 1993-04-05 | 1993-12-28 | General Electric Company | Gas turbine engine lubrication system |
US20030163983A1 (en) * | 2002-03-01 | 2003-09-04 | Seda Jorge F. | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
Also Published As
Publication number | Publication date |
---|---|
US20050198941A1 (en) | 2005-09-15 |
CN100470041C (zh) | 2009-03-18 |
EP1564397B1 (fr) | 2006-09-13 |
JP2005226643A (ja) | 2005-08-25 |
US7412819B2 (en) | 2008-08-19 |
FR2866074B1 (fr) | 2006-04-28 |
FR2866074A1 (fr) | 2005-08-12 |
CN1654805A (zh) | 2005-08-17 |
DE602005000116T2 (de) | 2007-04-05 |
RU2005103601A (ru) | 2006-07-20 |
DE602005000116D1 (de) | 2006-10-26 |
UA83346C2 (uk) | 2008-07-10 |
RU2357092C2 (ru) | 2009-05-27 |
CA2495594C (fr) | 2012-01-10 |
CA2495594A1 (fr) | 2005-08-11 |
ES2271935T3 (es) | 2007-04-16 |
EP1564397A1 (fr) | 2005-08-17 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4646644B2 (ja) | 前部に二つのファンを有するターボジェット構造 | |
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 | |
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 | |
US7487630B2 (en) | Jet engine with compact arrangement of fan | |
JP5662629B2 (ja) | ターボファンエンジンアセンブリ | |
JP5155648B2 (ja) | ターボファンエンジンアセンブリ | |
JP5965691B2 (ja) | ターボファンエンジンアセンブリ | |
JP4204349B2 (ja) | ガスタービンエンジンのための二重反転可能なブースタ圧縮機組立体 | |
US7926259B2 (en) | Turbofan engine assembly and method of assembling same | |
JP4906311B2 (ja) | 二重反転ガスタービンエンジン及びそれを組立てる方法 | |
US7905083B2 (en) | Turbofan engine assembly and method of assembling same | |
US7882693B2 (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 | |
EP1626002B1 (en) | Gas turbine engine turbine assembly | |
US7290386B2 (en) | Counter-rotating gas turbine engine and method of assembling same | |
JP2008032016A (ja) | ガスタービンエンジンアセンブリ | |
CN104884761B (zh) | 可变喷嘴单元及可变容量型增压器 | |
JP5644302B2 (ja) | 軸流圧縮機及びガスタービンエンジン |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20071227 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20100511 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20100806 |
|
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: 20101116 |
|
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: 20101207 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20131217 Year of fee payment: 3 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 4646644 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
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 |