JP5220371B2 - パイロンが一体化されてなる航空機用推進システム - Google Patents
パイロンが一体化されてなる航空機用推進システム Download PDFInfo
- Publication number
- JP5220371B2 JP5220371B2 JP2007241952A JP2007241952A JP5220371B2 JP 5220371 B2 JP5220371 B2 JP 5220371B2 JP 2007241952 A JP2007241952 A JP 2007241952A JP 2007241952 A JP2007241952 A JP 2007241952A JP 5220371 B2 JP5220371 B2 JP 5220371B2
- Authority
- JP
- Japan
- Prior art keywords
- propulsion system
- nacelle
- cylindrical portion
- downstream
- 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.)
- Active
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 17
- 238000012423 maintenance Methods 0.000 claims description 2
- 239000000725 suspension Substances 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000004873 anchoring Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
-
- 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
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
- Y02T50/40—Weight reduction
-
- 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)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Wind Motors (AREA)
Description
12 ターボジェット
16 上流側円筒部分
18 中間円筒部分
20 下流側円筒部分
22 支持構造体
24 骨組み
26 梁
28 エンジンを航空機へと固定するための部材
30 上流側の環状フランジ
32 中間ケース
34 アクセス開口
36、54、56 長手部材
38、50 環
40 排気ケース
42、52 リンク棒
46 骨組み
48 環状部品
58 環状フランジ
60、61 カウル
62 シュラウド
Claims (19)
- 一体型の推進システムであって、
バイパスターボジェットエンジンと、中間ケース(32)によって支えられてターボジェット(12)の周囲にバイパス空気の流れのための環状の空間を画定するナセル(10)とを備え、
ナセルが、剛であって上流側の端部に中間ケース(32)の外周の少なくとも180°にわたる環状の取り付けフランジ(30、58)を備えた下流側円筒部分を備え、
この円筒部分(20)が、ターボジェットの排気ケース(40)をこの円筒部分の下流側の端部において支持および案内するとともに、エンジンを航空機の一部分(22)へと固定するための部材(28)を取り付けるための手段(26)を備える、推進システム。 - 固定部材を取り付けるための手段(26)が、ナセルの下流側円筒部分(20)へと取り付けられ、あるいはナセルの下流側円筒部分の追加の厚さとして形成された、長手方向の梁からなる、請求項1に記載の推進システム。
- エンジンを航空機へと固定するための部材(28)は、両端部が前記長手方向の梁および航空機の一部分(22)へとそれぞれ固定されるリンク棒または接続ロッドである、請求項2に記載の推進システム。
- ナセルの下流側円筒部分(20)が、バイパス空気を案内するための外壁を構成している、請求項1から3のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分の上流側の環状フランジ(30)が、360°にわたって中間ケース(32)へと取り付けられている、請求項1から4のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分の下流側の端部(38、50)が、リンク棒または接続ロッド(42、52)ならびに排気ケースの軸方向および半径方向の膨張を許容する手段によって、排気ケース(40)へと接続されている、請求項1から5のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分の下流側の端部が、航空機の一部へのエンジン固定部材を取り付けるための手段(54)へと取り付けられたリンク棒または接続ロッドによって、排気ケース(40)へと接続されている、請求項6に記載の推進システム。
- 排気ケース(40)と航空機へのエンジン取り付け手段を固定するための手段(54)との間に、排気ケースの軸方向に見てV字を形成する、2つのリンク棒または接続ロッドを備えている、請求項7に記載の推進システム。
- ナセルの下流側円筒部分が、フェアリングまたはカウリングのパネルが取り付けられる骨組み(24)を備える、請求項1から8のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分が、ターボジェットの構成要素へのアクセスを提供するアクセス開口およびこれらの開口を閉じるためのパネルを備える、請求項1から9のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分の下流側の端部が、排気ケースを囲んでリンクまたは接続ロッドによってナセルの下流側円筒部分へと接続する補助ケースを介して、排気ケース(40)を支持する、請求項1から10のいずれか一項に記載の推進システム。
- バイパス空気を案内するための半径方向内側の壁を形成する円筒形のシュラウド(62)が、その上流端において中間ケースへと取り付けられ、その下流端において排気ケースへと、この排気ケースの軸方向および半径方向の膨張を許容する手段によって接続されている、請求項1から11のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分の穴あき構造を通ってバイパス空気を偏向させることによって推力を反転させるための手段を備える、請求項1から12のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分が、穴あき構造(48)を閉じる位置と、この穴あき構造(48)を露出させて逆推力装置の動作を可能にする位置との間を移動できるカウリングパネル(60)を備える、請求項13に記載の推進システム。
- ナセルの下流側円筒部分が、逆推力装置の動作を可能にするためおよび保守を容易にするために、軸方向にスライド可能に取り付けられた円筒ダクトによって形成されるカウル(61)を備える、請求項8に記載の推進システム。
- 推力反転手段を備え、該推力反転手段のカスケード(64)が前記ナセルの下流側円筒部分の上流の細長い中間ケースに収容されている、請求項1から12のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分が、エンジンを航空機へと固定するための手段を取り付けるための手段を備えた外側の長手方向の梁(26、54)を備えるとともに、エンジンの中間ケースの外周の少なくとも180°にわたる環状の取り付けフランジ(30)を一端に備える、請求項1から16のいずれか一項に記載の推進システム。
- ナセルの下流側円筒部分が、逆推力装置の出口カスケードが取り付けられる格子を形成する穴あきの端部(48)を備える、請求項17に記載の推進システム。
- ナセルの下流側円筒部分が、穴あきの端部(48)を閉じる位置とこの穴あきの端部を露出させる位置との間を移動できるように取り付けられたカウリングパネル(60)を備える、請求項18に記載の推進システム。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0608216A FR2905990A1 (fr) | 2006-09-20 | 2006-09-20 | Systeme propulsif a pylone integre pour avion. |
FR0608216 | 2006-09-20 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008101612A JP2008101612A (ja) | 2008-05-01 |
JP5220371B2 true JP5220371B2 (ja) | 2013-06-26 |
Family
ID=37913162
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007241952A Active JP5220371B2 (ja) | 2006-09-20 | 2007-09-19 | パイロンが一体化されてなる航空機用推進システム |
Country Status (7)
Country | Link |
---|---|
US (1) | US7938359B2 (ja) |
EP (1) | EP1902951B1 (ja) |
JP (1) | JP5220371B2 (ja) |
CA (1) | CA2602176C (ja) |
DE (1) | DE602007002678D1 (ja) |
FR (1) | FR2905990A1 (ja) |
RU (1) | RU2440279C2 (ja) |
Families Citing this family (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2914907B1 (fr) * | 2007-04-16 | 2009-10-30 | Snecma Sa | Suspension souple avec peigne pour turbomoteur |
FR2917710A1 (fr) * | 2007-06-22 | 2008-12-26 | Aircelle Sa | Platine de fixation et longeron de manutention d'ensemble propulsif monobloc d'un aeronef |
US8438859B2 (en) * | 2008-01-08 | 2013-05-14 | Rolls-Royce North American Technologies, Inc. | Integrated bypass engine structure |
FR2933070B1 (fr) * | 2008-06-25 | 2010-08-20 | Snecma | Systeme propulsif d'aeronef |
US8262050B2 (en) * | 2008-12-24 | 2012-09-11 | General Electric Company | Method and apparatus for mounting and dismounting an aircraft engine |
US8469309B2 (en) * | 2008-12-24 | 2013-06-25 | General Electric Company | Monolithic structure for mounting aircraft engine |
FR2941673B1 (fr) * | 2009-02-04 | 2011-01-14 | Aircelle Sa | Ensemble de suspension pour turboreacteur d'aeronef |
US8713910B2 (en) * | 2009-07-31 | 2014-05-06 | General Electric Company | Integrated thrust reverser/pylon assembly |
FR2950322B1 (fr) * | 2009-09-22 | 2012-05-25 | Airbus Operations Sas | Element d'accrochage d'un moteur d'aeronef, ensemble d'aeronef comprenant cet element et aeronef associe |
FR2950323B1 (fr) | 2009-09-22 | 2011-11-04 | Airbus Operations Sas | Mat d'accrochage de moteur d'aeronef, ensemble comprenant ce mat et aeronef associe |
FR2950860B1 (fr) | 2009-10-01 | 2011-12-09 | Airbus Operations Sas | Dispositif d'accrochage d'un moteur a un mat d'aeronef |
US8272595B2 (en) * | 2009-11-27 | 2012-09-25 | Rohr, Inc. | Fan cowl support for a turbofan engine |
US8398018B2 (en) * | 2009-11-27 | 2013-03-19 | Rohr, Inc. | Fan cowl support for a turbo fan engine |
GB201007215D0 (en) * | 2010-04-30 | 2010-06-16 | Rolls Royce Plc | Gas turbine engine |
FR2959726B1 (fr) * | 2010-05-07 | 2013-05-31 | Aircelle Sa | Ensemble pour systeme propulsif d'aeronef |
GB2481437B (en) * | 2010-06-25 | 2012-05-23 | Rolls Royce Plc | An assembly comprising a gas turbine engine and a supporting pylon |
FR2962765B1 (fr) * | 2010-07-13 | 2012-07-27 | Snecma | Turboreacteur avec un element de nacelle fixe au carter intermediaire |
US8549026B2 (en) * | 2010-10-12 | 2013-10-01 | Clinicomp International, Inc. | Standardized database access system and method |
GB2492107B (en) * | 2011-06-22 | 2013-09-04 | Rolls Royce Plc | Mounting assembly |
US9828105B2 (en) * | 2011-08-24 | 2017-11-28 | United Technologies Corporation | Nacelle assembly having integrated afterbody mount case |
US8567745B2 (en) * | 2011-12-15 | 2013-10-29 | United Technologies Corporation | Apparatuses and systems with vertically and longitudinally offset mounting flanges |
FR2994941B1 (fr) * | 2012-09-06 | 2015-08-07 | Airbus Operations Sas | Ensemble propulsif pour aeronef comprenant un carenage structural. |
CN102954318B (zh) * | 2012-11-08 | 2014-08-06 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种薄壁机匣新型加强筋布局设计方法 |
FR2997996B1 (fr) | 2012-11-12 | 2015-01-09 | Snecma | Support de tube d'evacuation d'air dans une turbomachine |
US9279342B2 (en) | 2012-11-21 | 2016-03-08 | General Electric Company | Turbine casing with service wedge |
US10006405B2 (en) | 2012-11-30 | 2018-06-26 | General Electric Company | Thrust reverser system with translating-rotating blocker doors and method of operation |
US9260281B2 (en) | 2013-03-13 | 2016-02-16 | General Electric Company | Lift efficiency improvement mechanism for turbine casing service wedge |
WO2015010315A1 (en) | 2013-07-26 | 2015-01-29 | Mra Systems, Inc. | Aircraft engine pylon |
GB201322077D0 (en) * | 2013-12-13 | 2014-01-29 | Rolls Royce Plc | Engine mount |
FR3044719B1 (fr) | 2015-12-08 | 2017-12-22 | Snecma | Ensemble de propulsion d'aeronef equipe de marches permettant a un operateur d'atteindre sa portion superieure |
FR3106126B1 (fr) * | 2020-01-10 | 2022-01-07 | Safran Aircraft Engines | Assemblage entre un pylône d’aéronef et une turbomachine |
US11585274B2 (en) | 2020-12-28 | 2023-02-21 | General Electric Company | Turbine rear frame link assemblies for turbofan engines |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3058302A (en) * | 1955-02-07 | 1962-10-16 | Avro Aircraft Ltd | Means inducing a flow of cooling air for gas turbine engines |
US3059426A (en) * | 1957-03-22 | 1962-10-23 | Marquardt Corp | Thrust reverser utilizing aft end mechanical blockage |
US2943449A (en) * | 1958-07-07 | 1960-07-05 | United Aircraft Corp | Bypass engine with flexible duct structure |
US3848832A (en) * | 1973-03-09 | 1974-11-19 | Boeing Co | Aircraft engine installation |
US4055041A (en) * | 1974-11-08 | 1977-10-25 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Integrated gas turbine engine-nacelle |
US4043522A (en) * | 1975-12-22 | 1977-08-23 | The Boeing Company | Common pod for housing a plurality of different turbofan jet propulsion engines |
US4044973A (en) * | 1975-12-29 | 1977-08-30 | The Boeing Company | Nacelle assembly and mounting structures for a turbofan jet propulsion engine |
US4266741A (en) * | 1978-05-22 | 1981-05-12 | The Boeing Company | Mounting apparatus for fan jet engine having mixed flow nozzle installation |
US4213585A (en) * | 1978-05-22 | 1980-07-22 | The Boeing Company | Mounting system for a wing mounted aircraft engine |
US4859143A (en) * | 1987-07-08 | 1989-08-22 | United Technologies Corporation | Stiffening ring for a stator assembly of an axial flow rotary machine |
US4922711A (en) * | 1988-06-10 | 1990-05-08 | The Boeing Company | Thrust reversing system for high bypass fan engines |
GB9116986D0 (en) * | 1991-08-07 | 1991-10-09 | Rolls Royce Plc | Gas turbine engine nacelle assembly |
US5350136A (en) * | 1993-05-14 | 1994-09-27 | United Technologies Corporation | Nacelle arrangement |
GB2384827A (en) * | 2002-01-30 | 2003-08-06 | Rolls Royce Plc | A Fastening Between The C-Duct and Core of a Ducted Fan Gas Turbine Engine. |
FR2873988B1 (fr) * | 2004-08-05 | 2007-12-21 | Airbus France Sas | Mat d'accrochage de turboreacteur pour aeronef |
FR2885877B1 (fr) * | 2005-05-23 | 2008-12-12 | Airbus France Sas | Mat d'accrochage de turboreacteur pour aeronef |
-
2006
- 2006-09-20 FR FR0608216A patent/FR2905990A1/fr not_active Withdrawn
-
2007
- 2007-08-16 DE DE602007002678T patent/DE602007002678D1/de active Active
- 2007-08-16 EP EP07291018A patent/EP1902951B1/fr active Active
- 2007-09-18 CA CA2602176A patent/CA2602176C/fr active Active
- 2007-09-19 RU RU2007134894/11A patent/RU2440279C2/ru active
- 2007-09-19 US US11/857,735 patent/US7938359B2/en active Active
- 2007-09-19 JP JP2007241952A patent/JP5220371B2/ja active Active
Also Published As
Publication number | Publication date |
---|---|
JP2008101612A (ja) | 2008-05-01 |
CA2602176C (fr) | 2014-10-28 |
RU2007134894A (ru) | 2009-03-27 |
CA2602176A1 (fr) | 2008-03-20 |
EP1902951B1 (fr) | 2009-10-07 |
US20080067287A1 (en) | 2008-03-20 |
FR2905990A1 (fr) | 2008-03-21 |
DE602007002678D1 (de) | 2009-11-19 |
US7938359B2 (en) | 2011-05-10 |
EP1902951A1 (fr) | 2008-03-26 |
RU2440279C2 (ru) | 2012-01-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP5220371B2 (ja) | パイロンが一体化されてなる航空機用推進システム | |
JP5363715B2 (ja) | バイパスターボジェットエンジンを備える一体型推進システム | |
JP4980221B2 (ja) | 軸受支持構造体、及び軸受支持構造体を有するガスタービンエンジン | |
US8876042B2 (en) | Integrated nacelle assembly | |
US8739552B2 (en) | Structural nacelle | |
US8469309B2 (en) | Monolithic structure for mounting aircraft engine | |
US8727269B2 (en) | System and method for mounting an aircraft engine | |
US8733693B2 (en) | Aircraft engine assembly comprising an annular load-transfer structure surrounding the central casing of a turbojet engine | |
US7770378B2 (en) | Turbofan case and method of making | |
US7430852B2 (en) | Turbojet having a large bypass ratio | |
US20050109013A1 (en) | Turbofan case and method of making | |
US8881536B2 (en) | Aircraft engine assembly comprising a turbojet engine with reinforcing structures connecting the fan casing to the central casing | |
US10759541B2 (en) | Nacelle bifurcation with leading edge structure | |
US10883447B2 (en) | Aircraft propulsion unit having thrust reverser flaps connected to an inter-compressor casing located between the engine compressors |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20100831 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20110816 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20111114 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20111117 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20120215 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20120410 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20120625 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20120628 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20121009 |
|
RD02 | Notification of acceptance of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7422 Effective date: 20121106 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20121207 |
|
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: 20130219 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20130306 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20160315 Year of fee payment: 3 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 5220371 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 |