JP2017150478A - 逆推力エンジン - Google Patents
逆推力エンジン Download PDFInfo
- Publication number
- JP2017150478A JP2017150478A JP2017019234A JP2017019234A JP2017150478A JP 2017150478 A JP2017150478 A JP 2017150478A JP 2017019234 A JP2017019234 A JP 2017019234A JP 2017019234 A JP2017019234 A JP 2017019234A JP 2017150478 A JP2017150478 A JP 2017150478A
- Authority
- JP
- Japan
- Prior art keywords
- core
- engine
- casing
- along
- core 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.)
- Granted
Links
- 230000002441 reversible effect Effects 0.000 title claims abstract description 36
- 239000012530 fluid Substances 0.000 claims description 7
- 238000002485 combustion reaction Methods 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 14
- 238000000034 method Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
- F02K1/68—Reversers mounted on the engine housing downstream of the fan exhaust section
-
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/30—Non-positive-displacement machines or engines, e.g. steam turbines characterised by having a single rotor operable in either direction of rotation, e.g. by reversing of blades
-
- 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
- F01D7/00—Rotors with blades adjustable in operation; Control thereof
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
- F02K1/66—Reversing fan flow using reversing fan blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/76—Control or regulation of thrust reversers
- F02K1/766—Control or regulation of thrust reversers with blocking systems or locking devices; Arrangement of locking devices for thrust reversers
-
- 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
- F02K3/075—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 controlling flow ratio between flows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- 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
Abstract
【解決手段】推進装置は、コアエンジン16と、コアケーシング18と、を含むことができる。コアエンジン16は、中心軸12に沿って延びるエンジンシャフトを含むことができる。コアケーシング18は、内面26及び外面24を有することができる。コアケーシング18は、推進装置の周りで円周方向に沿って、並びに前方端20から後方端22まで中心軸12に沿って延びることができる。コアケーシング18は、前方端20において環状入口28と後方端22において排気口32とを有する一次空気流路50を定めることができる。コアケーシング18は更に、外面入口から内面出口まで延びる逆流通路を定めることができる。
【選択図】図1
Description
12 中心線(中心軸)
14 ファンセクション
16 コアタービンエンジン
18 コアケーシング
20 前方端(コアケーシングの)
22 後方端(コアケーシングの)
24 外面(コアケーシングの)
26 内面(コアケーシングの)
28 環状コア入口
32 ジェット排気口
34 LP圧縮機
36 HP圧縮機
38 燃焼セクション
40 HPタービン
42 LPタービン
44 ジェット排気ノズル
46 HPシャフト
48 LPシャフト
50 一次空気流路
52 可変ピッチファン
54 ファンブレード
56 ファンブレードディスク
58 出力ギアボックス
59 空気流
60 ピッチ変更機構
62 ナセル
63 カウル入口
64 ファンカウル
65 バイパス排気口
66 出口ガイドベーン
68 バイパス空気流通路
70 空気流
72 空気流
74 ファン出口ステータベーン
76 コアストラット
78 内部固定支持体
80 半径方向支持ライン
82 逆流通路
84 連続ストリップ
86 外面入口
88 内面出口
90 逆方向空気流
92 逆方向空気流
94 逆方向空気流
96 能動的制御プレート
R 半径方向軸
P1 枢動軸
A 軸方向
Claims (10)
- 中心軸(12)と円周方向を定める推進装置であって、前記推進装置が、
前記中心軸(12)に沿って延びるエンジンシャフトを有するコアエンジン(16)と、
内面(26)及び外面(24)を有するコアケーシング(18)と、
を備え、
前記コアケーシング(18)が、前記推進装置の周りで円周方向に沿って延び且つ前方端(20)から後方端(22)まで前記中心軸(12)に沿って延び、前記コアケーシング(18)が、前記前方端(20)において環状入口(28)と前記後方端(22)において排気口(32)とを有する一次空気流路(50)を定め、前記コアケーシング(18)が更に、外面入口(86)から内面出口(88)まで延びる逆流通路(82)を定める、推進装置。 - 前記コアエンジン(16)が、
前記エンジンシャフトに取り付けられた圧縮機と、
前記圧縮機の下流側に位置付けられ、前記圧縮機からの圧縮流体を受け取る燃焼セクションと、
前記エンジンシャフトに取り付けられ且つ前記燃焼セクションの下流側に位置付けられて、前記エンジンを通じて前記圧縮機に回転力を提供するよう構成されたタービンと、
を含み、前記逆流通路(82)が、前記圧縮機の上流側の位置から前記圧縮機内に空気を配向するため前記コアケーシング(18)を通る弓状流路を定める、請求項1に記載の推進装置。 - 前記コアエンジン(16)が更に半径方向を定め、該コアエンジン(16)が更に、
前記半径方向に沿って前記コアケーシング(18)の内面(26)から内向きに延び、前記中心軸(12)に沿って前記環状入口(28)と前記内面出口(88)との間に位置付けられたコアストラット(76)と、
前記コアケーシング(18)の内面(26)から前記半径方向に沿って内向きに延び、前記中心軸(12)に沿って前記環状入口(28)と前記コアストラット(76)との間に位置付けられたステータベーン(74)と、
前記半径方向に沿って前記コアケーシング(18)の外面(24)から外向きに延び、前記中心軸(12)に沿って前記コアストラット(76)と整列されて堅固な半径方向支持ライン(80)を形成するバイパス出口ガイドベーン(66)と、
を含む、請求項1に記載の推進装置。 - 前記逆流通路(82)を通る空気を選択的に遮断するよう前記コアケーシング(18)に取り付けられた能動的制御プレート(96)を更に備える、請求項1に記載の推進装置。
- 前記円周方向に沿って離間して配置された複数の逆流通路(82)を更に備え、前記コアケーシング(18)が、前記逆流通路(82)の各々の間で前記コアケーシング(18)に沿って連続ストリップ(84)を定め、前記逆流通路(82)の各々が、前記外面(24)内に定められた開口から前記内面(26)内に定められた開口まで延びる、請求項1に記載の推進装置。
- 中心軸(12)を定めるエンジン(10)であって、
前方推力及び逆推力を発生させるための複数の可変ピッチファンブレード(54)を含むファンセクション(14)と、
前記ファンセクション(14)に駆動可能に接続されたコアエンジン(16)と、
前記コアエンジン(16)を密閉し、前記コアエンジン(16)を通る一次空気流路(50)を少なくとも部分的に定めるコアケーシング(18)と、
を備え、前記コアケーシング(18)が、前方端(20)から後方端(22)まで前記中心軸(12)に沿って延び、
前記コアケーシング(18)が、前記前方端(20)において前記一次空気流路(50)への環状入口(28)と、前記コアケーシング(18)を通って前記一次空気流路(50)に延びて、前記可変ピッチファンブレード(54)が逆推力を発生させたときに空気の流れが通過可能になる逆流通路(82)とを定める、エンジン(10)。 - 前記エンジンが更に円周方向を定め、
前記エンジン(10)が更に、前記ファンブレード(54)及び上記コアケーシング(18)の少なくとも一部の周りで円周方向に沿って延びる連続ファンケーシングを備え、前記連続ファンケーシングが、該連続ファンケーシングと前記コアケーシング(18)との間にバイパス空気流通路(68)を定める、請求項6に記載のエンジン(10)。 - 前記エンジンが更に半径方向を定め、該エンジンが更に、
前記半径方向に沿って前記コアケーシング(18)の内面(26)から内向きに延び、前記中心軸(12)に沿って前記環状入口(28)と前記内面出口(88)との間に位置付けられたコアストラット(76)と、
前記コアケーシング(18)の内面(26)から前記半径方向に沿って内向きに延び、前記中心軸(12)に沿って前記環状入口(28)と前記コアストラット(76)との間に位置付けられたステータベーン(74)と、
前記半径方向に沿って前記コアケーシング(18)の外面(24)から外向きに延び、前記中心軸(12)に沿って前記コアストラット(76)と整列されて堅固な半径方向支持ライン(80)を形成するバイパス出口ガイドベーン(66)と、
を備える、請求項6に記載のエンジン(10)。 - 前記逆流通路(82)を通る空気を選択的に遮断するよう前記コアケーシング(18)に取り付けられた能動的制御プレート(96)を更に備える、請求項6に記載のエンジン(10)。
- 前記エンジンが更に円周方向を定め、該エンジンが更に、
前記円周方向に沿って離間して配置された複数の逆流通路(82)を備え、前記コアケーシング(18)が、前記逆流通路(82)の各々の間で前記コアケーシング(18)に沿って連続ストリップ(84)を定める、請求項6に記載のエンジン(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/018,893 | 2016-02-09 | ||
US15/018,893 US10502160B2 (en) | 2016-02-09 | 2016-02-09 | Reverse thrust engine |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2017150478A true JP2017150478A (ja) | 2017-08-31 |
JP6484262B2 JP6484262B2 (ja) | 2019-03-13 |
Family
ID=57984831
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2017019234A Active JP6484262B2 (ja) | 2016-02-09 | 2017-02-06 | 逆推力エンジン |
Country Status (5)
Country | Link |
---|---|
US (1) | US10502160B2 (ja) |
EP (1) | EP3205868B1 (ja) |
JP (1) | JP6484262B2 (ja) |
CN (1) | CN107044359A (ja) |
CA (1) | CA2956985C (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20230005809A (ko) | 2020-04-30 | 2023-01-10 | 쿠미아이카가꾸고오교오가부시끼가이샤 | 모노설폭사이드 유도체의 제조 방법 |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3057620B1 (fr) * | 2016-10-18 | 2020-07-31 | Safran Aircraft Engines | Ensemble propulsif comprenant un conduit d'alimentation du generateur de gaz dans un carter inter-veine |
FR3100268B1 (fr) * | 2019-08-29 | 2022-12-30 | Safran Aircraft Engines | Turbomachine a double flux pour un aeronef |
US11668253B2 (en) * | 2020-10-16 | 2023-06-06 | Pratt & Whitney Canada Corp. | System and method for providing in-flight reverse thrust for an aircraft |
GB202210039D0 (en) | 2022-05-20 | 2022-08-24 | Rolls Royce Plc | Gas turbine engine |
GB202210040D0 (en) | 2022-05-20 | 2022-08-24 | Rolls Royce Plc | Gas turbine engine |
US20240026829A1 (en) * | 2022-07-22 | 2024-01-25 | Raytheon Technologies Corporation | Multi-duct exhaust system for gas turbine engine |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3476486A (en) * | 1966-04-12 | 1969-11-04 | Dowty Rotol Ltd | Gas turbine engines |
US3589132A (en) * | 1969-06-04 | 1971-06-29 | Garrett Corp | Gas turbine engine |
US3897001A (en) * | 1974-06-12 | 1975-07-29 | Gen Electric | Nozzle and auxiliary inlet arrangement for gas turbine engine |
US4005574A (en) * | 1975-04-21 | 1977-02-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Reverse pitch fan with divided splitter |
US4047911A (en) * | 1973-04-12 | 1977-09-13 | Dornier Gmbh | Air intake with deflecting device against foreign objects impinging in the initial direction of air flow at engine nacelles |
US4371132A (en) * | 1980-01-11 | 1983-02-01 | Rolls Royce Limited | Reversible thrust ducted fan propulsion unit |
US20160017752A1 (en) * | 2009-11-20 | 2016-01-21 | United Technologies Corporation | Turbofan Engine Assembly Methods |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2746671A (en) * | 1950-04-14 | 1956-05-22 | United Aircraft Corp | Compressor deicing and thrust balancing arrangement |
DE1628240A1 (de) * | 1966-04-12 | 1971-07-08 | Dowty Rotol Ltd | Vorrichtung zur Schaufelverstellung bei Geblaesen |
GB1319793A (ja) * | 1970-11-19 | 1973-06-06 | ||
GB1418905A (en) | 1972-05-09 | 1975-12-24 | Rolls Royce | Gas turbine engines |
GB1497477A (en) * | 1975-07-19 | 1978-01-12 | Rolls Royce | Gas turbine engine |
GB2070691B (en) * | 1980-01-11 | 1983-08-24 | Rolls Royce | Radial splitter for reversible pitch fan propulsion unit |
DE4039810C1 (ja) | 1990-12-13 | 1991-10-17 | Mtu Muenchen Gmbh | |
US6042053A (en) | 1997-10-31 | 2000-03-28 | The Boeing Company | Automatic restow system for aircraft thrust reverser |
FR2914954B1 (fr) | 2007-04-13 | 2012-12-07 | Snecma | Turboreacteur a double flux comportant un inverseur de poussee. |
US8708643B2 (en) | 2007-08-14 | 2014-04-29 | General Electric Company | Counter-rotatable fan gas turbine engine with axial flow positive displacement worm gas generator |
FR2946395B1 (fr) | 2009-06-04 | 2016-03-04 | Airbus France | Procede pour la detection de l'ouverture d'un inverseur de poussee de turboreacteur d'aeronef |
GB201219368D0 (en) | 2012-10-29 | 2012-12-12 | Rolls Royce Deutschland | Aeroengine thrust reverser arrangement |
WO2014113372A1 (en) | 2013-01-18 | 2014-07-24 | General Electric Company | Engine architecture with reverse rotation integral drive and vaneless turbine |
FR3057620B1 (fr) * | 2016-10-18 | 2020-07-31 | Safran Aircraft Engines | Ensemble propulsif comprenant un conduit d'alimentation du generateur de gaz dans un carter inter-veine |
-
2016
- 2016-02-09 US US15/018,893 patent/US10502160B2/en active Active
-
2017
- 2017-02-02 CA CA2956985A patent/CA2956985C/en active Active
- 2017-02-06 JP JP2017019234A patent/JP6484262B2/ja active Active
- 2017-02-06 EP EP17154880.3A patent/EP3205868B1/en active Active
- 2017-02-09 CN CN201710070769.4A patent/CN107044359A/zh active Pending
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3476486A (en) * | 1966-04-12 | 1969-11-04 | Dowty Rotol Ltd | Gas turbine engines |
US3589132A (en) * | 1969-06-04 | 1971-06-29 | Garrett Corp | Gas turbine engine |
US4047911A (en) * | 1973-04-12 | 1977-09-13 | Dornier Gmbh | Air intake with deflecting device against foreign objects impinging in the initial direction of air flow at engine nacelles |
US3897001A (en) * | 1974-06-12 | 1975-07-29 | Gen Electric | Nozzle and auxiliary inlet arrangement for gas turbine engine |
US4005574A (en) * | 1975-04-21 | 1977-02-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Reverse pitch fan with divided splitter |
US4371132A (en) * | 1980-01-11 | 1983-02-01 | Rolls Royce Limited | Reversible thrust ducted fan propulsion unit |
US20160017752A1 (en) * | 2009-11-20 | 2016-01-21 | United Technologies Corporation | Turbofan Engine Assembly Methods |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20230005809A (ko) | 2020-04-30 | 2023-01-10 | 쿠미아이카가꾸고오교오가부시끼가이샤 | 모노설폭사이드 유도체의 제조 방법 |
Also Published As
Publication number | Publication date |
---|---|
JP6484262B2 (ja) | 2019-03-13 |
CN107044359A (zh) | 2017-08-15 |
EP3205868A1 (en) | 2017-08-16 |
CA2956985A1 (en) | 2017-08-09 |
US10502160B2 (en) | 2019-12-10 |
EP3205868B1 (en) | 2019-05-22 |
US20170226960A1 (en) | 2017-08-10 |
CA2956985C (en) | 2019-06-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP6484262B2 (ja) | 逆推力エンジン | |
JP2016211571A (ja) | 可変ピッチ出口ガイドベーンを有するタービンエンジン | |
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 | |
US10082079B2 (en) | Gas-turbine engine with oil cooler in the engine cowling | |
US10508546B2 (en) | Turbomachine with alternatingly spaced turbine rotor blades | |
JP4463810B2 (ja) | 航空機用エンジン装置 | |
US20170191449A1 (en) | Efficient, low pressure ratio propulsor for gas turbine engines | |
JP2017096269A (ja) | ガスタービンエンジンファン | |
JP6183934B2 (ja) | タービンエンジンの熱管理システム | |
US10823064B2 (en) | Gas turbine engine | |
US9121412B2 (en) | Efficient, low pressure ratio propulsor for gas turbine engines | |
US11098592B2 (en) | Turbomachine with alternatingly spaced turbine rotor blades | |
JP2017072136A (ja) | 可変ピッチ出口ガイドベーンを有するエンジン | |
JP2010174887A (ja) | ガスタービエンジン組立体及びそれを組立てる方法 | |
JP2017160902A (ja) | 一体型ピッチ制御機構アクチュエータの作動流体移送のための方法およびシステム | |
JP2017106465A (ja) | ガスタービンエンジン | |
JP2019095184A (ja) | ガスタービンエンジン用の渦停留型燃焼器における接線方向バルク旋回空気 | |
CN113217582A (zh) | 用于发动机的齿轮箱 | |
EP3623283B1 (en) | Turbomachine | |
JP6612369B2 (ja) | 複数の排出ポートを有するギヤボックスのための装置 | |
EP3617059B1 (en) | Turbomachine | |
EP3623285B1 (en) | Turbomachine | |
EP3623282B1 (en) | Turbomachine | |
CN114651120A (zh) | 燃气涡轮发动机 | |
BR102016028946A2 (pt) | Gas turbine motors |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20180306 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20180605 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20180821 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20181219 |
|
A911 | Transfer to examiner for re-examination before appeal (zenchi) |
Free format text: JAPANESE INTERMEDIATE CODE: A911 Effective date: 20181226 |
|
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: 20190122 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20190215 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 6484262 Country of ref document: JP 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 |