JP2009150385A - 航空機用ジェットエンジンの中間ケーシングの延長具であって、ナセルカバーを受け入れるための環状の溝がセクタに分けられている延長具 - Google Patents
航空機用ジェットエンジンの中間ケーシングの延長具であって、ナセルカバーを受け入れるための環状の溝がセクタに分けられている延長具 Download PDFInfo
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- 239000000463 material Substances 0.000 claims description 13
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 230000000295 complement effect Effects 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 239000004606 Fillers/Extenders Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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Classifications
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- 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
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
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- 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
- F02K3/06—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 fan
-
- 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
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Tires In General (AREA)
Abstract
【解決手段】航空機用ジェットエンジンの中間ケーシングの延長具(30)であって、中間ケーシングの外殻から下流端に向かって突き出すように意図されており、ナセルカバーを受け入れるように意図された半径方向外側に向かって開いている環状の溝(66)を形成する接続用の環状の下流端(64)を備える延長具に関する。本発明によれば、接続用の環状の下流端(64)が、複数の角度セクタ(76a、76b)を用いて製造される。
【選択図】図7
Description
2 ジェットエンジン
4 取り付け支柱
5 長手軸
6a 前部エンジン取り付け具
6b 後部エンジン取り付け具
7 前後方向
8 カプラ
10 取り付け手段
11 剛構造
12 ファンケーシング
16 中央ケーシング
17 構造アーム
19 (中央ケーシングの)後端
21 中間ケーシング
23 外殻
25、27 横プレート
30 延長具
32 ナセル
34 空気導入口
36 ファンカバー
38 逆推力装置カバー、ナセルカバー
40 後部カウリング
42 二次流路
44 外側の環状の外板
46 内側の環状の外板
48 (逆推力装置カバーの)上端
50 (逆推力装置カバーの)下端
52 開口、ハウジング
54 ドア
56 ピン
58 受け穴
60 ラム
62 矢印(逆流)
64 接続用の環状の下流端
66 環状の溝
68 リブ
70 リング
72 構造アーム
74 接合シェル
75 カラー
76a、76b、86 角度セクタ
78 ねじ
80 ナット
82 貫通穴
90 延長具セクタ
Claims (10)
- 航空機用ジェットエンジンの中間ケーシング(21)の外殻(23)から下流端に向かって突き出すように意図されており、ナセルカバー(38)を受け入れるように意図された半径方向外側に向かって開いている環状の溝(66)を形成する接続用の環状の下流端(64)を備える延長具(30)であって、
前記接続用の環状の下流端(64)が、複数の角度セクタ(76a、76b)を用いて製造されていることを特徴とする、延長具。 - 角度セクタ(76a、76b)の数が、3以上であることを特徴とする、請求項1に記載の延長具。
- 前記接続用の環状の下流端(64)を形成する前記角度セクタ(76a、76b)へと固定される接合シェル(74)をさらに備え、
該シェルが、前記角度セクタの上流に位置し、中間ケーシングの外殻(23)の下流端を延長するように意図されていることを特徴とする、請求項1または2に記載の延長具。 - 前記接合シェル(74)が、前記接続用の環状の下流端を形成する角度セクタ(76a、76b)が取り付けられる単一の部品にて製造されていることを特徴とする、請求項3に記載の延長具。
- 前記接続用の環状の下流端を形成する角度セクタ(76a、76b)が、ねじ留めによって前記接合シェル(74)に取り付けられていることを特徴とする、請求項4に記載の延長具。
- 前記接合シェル(74)が、複数の角度セクタ(86)によって製造されており、それぞれの角度セクタ(86)が、前記接続用の環状の下流端(64)を形成する前記角度セクタ(76a、76b)のうちの1つと一緒に単一の部品にて製造されていることを特徴とする、請求項3に記載の延長具。
- 前記接続用の環状の下流端を形成する前記角度セクタ(76a、76b)が、前記周方向において交互に第1の材料および第2の材料から製造されていることを特徴とする、請求項1から6のいずれか一項に記載の延長具。
- 請求項1から7のいずれか一項に記載の延長具(30)を外殻(23)の下流端に具備している中間ケーシング(21)を備える、航空機用ジェットエンジン(2)。
- 請求項8に記載のジェットエンジン(2)、ならびに前記半径方向外側に向かって開いている環状の溝(66)と協働するナセルカバー(38)を備えるナセル(32)を備える、航空機用の推進アセンブリ(1)。
- 前記ジェットエンジンのための取り付け支柱(4)をさらに備え、
前記取り付け支柱(4)が、剛構造(11)と、前記ジェットエンジンを前記剛構造(11)へ取り付ける手段とを備え、
前記ナセルカバー(38)が、前記剛構造(11)へと関節接続されていることを特徴とする、請求項9に記載の推進アセンブリ。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0759939A FR2925120B1 (fr) | 2007-12-18 | 2007-12-18 | Extension de carter intermediaire pour turboreacteur d'aeronef, comprenant une rainure annulaire sectorisee de reception des capots de nacelle |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2009150385A true JP2009150385A (ja) | 2009-07-09 |
Family
ID=39456576
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008319255A Pending JP2009150385A (ja) | 2007-12-18 | 2008-12-16 | 航空機用ジェットエンジンの中間ケーシングの延長具であって、ナセルカバーを受け入れるための環状の溝がセクタに分けられている延長具 |
Country Status (6)
Country | Link |
---|---|
US (1) | US8172527B2 (ja) |
EP (1) | EP2072397B1 (ja) |
JP (1) | JP2009150385A (ja) |
CA (1) | CA2647439C (ja) |
FR (1) | FR2925120B1 (ja) |
RU (1) | RU2472677C2 (ja) |
Cited By (4)
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JP2012251556A (ja) * | 2011-06-06 | 2012-12-20 | General Electric Co <Ge> | 逆推力装置を取り付けるためのクランプシステム及びその方法 |
WO2015093201A1 (ja) * | 2013-12-20 | 2015-06-25 | 株式会社Ihi | ファンケース及びファンケースの製造方法 |
WO2016027368A1 (ja) * | 2014-08-22 | 2016-02-25 | 株式会社Ihi | 円筒状ケース |
JP2016532804A (ja) * | 2013-07-29 | 2016-10-20 | スネクマ | タービンエンジンケーシングおよび製造方法 |
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US20140174056A1 (en) * | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
US9114882B2 (en) * | 2010-10-26 | 2015-08-25 | United Technologies Corporation | Fan case and mount ring snap fit assembly |
FR2990001B1 (fr) * | 2012-04-27 | 2016-01-08 | Snecma | Assemblage d'un echangeur thermique au sein d'un carter intermediaire de turboreacteur |
FR2994216B1 (fr) | 2012-08-02 | 2014-09-05 | Snecma | Partie de revolution de carter intermediaire comportant un insert dispose dans une rainure annulaire |
US9211955B1 (en) * | 2012-12-10 | 2015-12-15 | The Boeing Company | Methods and apparatus for supporting engines and nacelles relative to aircraft wings |
FR2999651B1 (fr) | 2012-12-18 | 2015-01-16 | Snecma | Extension de carter intermediaire a conception amelioree |
FR3010048B1 (fr) * | 2013-09-04 | 2017-03-31 | Snecma | Structure de liaison moteur-nacelle a cales de liaison |
FR3010049B1 (fr) * | 2013-09-04 | 2017-03-31 | Snecma | Structure de liaison moteur-nacelle a secteurs de virole pivotants |
FR3011584B1 (fr) * | 2013-10-04 | 2018-02-23 | Safran Aircraft Engines | Extension de carter intermediaire |
US9669938B2 (en) * | 2015-01-16 | 2017-06-06 | United Technologies Corporation | Upper bifi frame for a gas turbine engine and methods therefor |
FR3033722B1 (fr) | 2015-03-18 | 2017-09-01 | Snecma | Outillage pour l'usinage d'une gorge d'un carter de turbomachine |
PL415487A1 (pl) * | 2015-12-31 | 2017-07-03 | General Electric Company | Formowana kompozytowa osłona chroniąca przed zużyciem krawędzi dla złącza w postaci wpustu V-kształtnego i łopatki V-kształtnej |
WO2017208117A1 (en) * | 2016-05-30 | 2017-12-07 | Bombardier Inc. | Aircraft engine assembly |
US10837305B2 (en) * | 2018-09-24 | 2020-11-17 | Kyle Albrecht | Hybrid jet engine |
FR3117173A1 (fr) * | 2020-12-09 | 2022-06-10 | Safran Aircraft Engines | Ensemble propulsif d’aéronef et procédé d’adaptation d’un ensemble propulsif |
FR3121709B1 (fr) | 2021-04-08 | 2023-05-05 | Safran Aircraft Engines | Virole extérieure de carter intermédiaire en matériau composite, pour turbomachine d’aéronef |
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- 2008-12-16 EP EP08171754.8A patent/EP2072397B1/fr active Active
- 2008-12-16 JP JP2008319255A patent/JP2009150385A/ja active Pending
- 2008-12-17 RU RU2008149987/11A patent/RU2472677C2/ru active
- 2008-12-17 CA CA2647439A patent/CA2647439C/en active Active
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JP2012251556A (ja) * | 2011-06-06 | 2012-12-20 | General Electric Co <Ge> | 逆推力装置を取り付けるためのクランプシステム及びその方法 |
JP2016532804A (ja) * | 2013-07-29 | 2016-10-20 | スネクマ | タービンエンジンケーシングおよび製造方法 |
WO2015093201A1 (ja) * | 2013-12-20 | 2015-06-25 | 株式会社Ihi | ファンケース及びファンケースの製造方法 |
JP2015121101A (ja) * | 2013-12-20 | 2015-07-02 | 株式会社Ihi | ファンケース及びファンケースの製造方法 |
US10280939B2 (en) | 2013-12-20 | 2019-05-07 | Ihi Corporation | Fan case and fan case manufacturing method |
WO2016027368A1 (ja) * | 2014-08-22 | 2016-02-25 | 株式会社Ihi | 円筒状ケース |
JPWO2016027368A1 (ja) * | 2014-08-22 | 2017-04-27 | 株式会社Ihi | 円筒状ケース |
US10294961B2 (en) | 2014-08-22 | 2019-05-21 | Ihi Corporation | Cylindrical case |
Also Published As
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US20090155070A1 (en) | 2009-06-18 |
US8172527B2 (en) | 2012-05-08 |
RU2008149987A (ru) | 2010-06-27 |
CA2647439C (en) | 2016-01-26 |
EP2072397B1 (fr) | 2015-02-11 |
RU2472677C2 (ru) | 2013-01-20 |
FR2925120B1 (fr) | 2010-02-19 |
EP2072397A3 (fr) | 2013-03-06 |
FR2925120A1 (fr) | 2009-06-19 |
CA2647439A1 (en) | 2009-06-18 |
EP2072397A2 (fr) | 2009-06-24 |
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