JP2016517927A - ジェットエンジン用の複数ノズル分流器 - Google Patents
ジェットエンジン用の複数ノズル分流器 Download PDFInfo
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- JP2016517927A JP2016517927A JP2016512928A JP2016512928A JP2016517927A JP 2016517927 A JP2016517927 A JP 2016517927A JP 2016512928 A JP2016512928 A JP 2016512928A JP 2016512928 A JP2016512928 A JP 2016512928A JP 2016517927 A JP2016517927 A JP 2016517927A
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- air
- stream
- duct
- turbofan engine
- engine
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- 239000012530 fluid Substances 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 11
- 238000004891 communication Methods 0.000 claims description 10
- 230000000903 blocking effect Effects 0.000 claims 1
- 239000000567 combustion gas Substances 0.000 abstract description 7
- 230000007246 mechanism Effects 0.000 description 10
- 239000000446 fuel Substances 0.000 description 6
- 239000007789 gas Substances 0.000 description 6
- 230000003416 augmentation Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000003190 augmentative effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003623 enhancer Substances 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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- 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
- F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
-
- 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
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- 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
- F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
-
- 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
- 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
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Jet Pumps And Other Pumps (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
Description
128 1次ノズル
132 第3のダクト
140 ダイバータバルブ
142 2次ノズル
144 拡大スロット
146 拡大フラップ&シール
A7 1次ノズル断面
A8 ノズルスロート
Claims (18)
- 3つの空気流ストリームをエンジンに提供するファン部分を有する航空機ターボファンエンジン(10)であって、
1次ノズル(128)を通じて排出されるコア空気流を受けるエンジンコアと、
バイパス空気ストリーム流れを受け取るバイパスダクト(18)と、
第3のストリーム空気流を受け取る第3の空気ダクト(132)と、
を備え、
前記第3のストリーム空気流が、前記第3の空気ダクトを通って流れ、前記第3の空気ダクトが空気入口と空気出口とを有し、前記第3の空気ダクトの空気出口が更に、2次ノズル(142)と、前記1次ノズル(128)と、前記2次ノズル又は前記1次ノズルの少なくとも一方に前記第3の空気流を配向する流れダイバータバルブ(140)とを含む、航空機ターボファンエンジン(10)。 - 前記1次ノズルを含む前記第3のストリーム空気流のための前記空気出口が更に、前記1次ノズルにおける拡大フラップ&シール(146)内に形成された拡大スロットに沿って前記流れダイバータバルブの間に流体連通を含む、請求項1に記載の航空機ターボファンエンジン(10)。
- 前記ダイバータバルブがパッシブバルブである、請求項1に記載の航空機ターボファンエンジン(10)。
- 前記パッシブダイバータバルブが、前記第3の空気ダクトにおける前記第3のストリーム空気の圧力により、前記1次ノズル及び前記2次ノズルへの流体連通を提供する第1の位置に付勢される、請求項3に記載の航空機ターボファンエンジン(10)。
- 前記1次ノズルへの前記第3のストリーム空気の流れが更に、前記拡大フラップ&シールに対して冷却を提供する、請求項4に記載の航空機ターボファンエンジン(10)。
- 前記パッシブダイバータバルブが、前記第3の空気ダクトにおける前記第3のストリーム空気の圧力に打ち克って、前記第3の空気ダクトと前記1次ノズルとの間の流体連通を遮断して前記第3のストリーム空気を前記2次ノズルにのみ配向する第2の位置に付勢される、請求項3に記載の航空機ターボファンエンジン(10)。
- 前記パッシブダイバータバルブが、前記1次ノズルから前記第3の空気ダクト内への高温ガスの逆流を遮断する第2の位置に付勢される、請求項6に記載の航空機ターボファンエンジン(10)。
- 前記ダイバータバルブがアクティブバルブである、請求項1に記載の航空機ターボファンエンジン(10)。
- 前記アクティブダイバータバルブが、該ダイバータバルブの位置を決定し制御するコントローラと通信状態にある、請求項8に記載の航空機ターボファンエンジン(10)。
- 前記第3の空気ダクトが更に、前記コントローラと通信状態で空気圧力を監視する圧力センサを含む、請求項9に記載の航空機ターボファンエンジン(10)。
- 前記コントローラは、前記第3の空気ダクト内の空気圧力が所定圧力を上回ったときに、前記2次ノズル及び前記1次ノズルの両方に流体連通を提供する前記ダイバータバルブの第1の位置を決定する、請求項10に記載の航空機ターボファンエンジン(10)。
- 前記コントローラは、前記第3の空気ダクト内の空気圧力が所定圧力以下になったときに、前記1次ノズルへの流体連通を遮断しながら、前記2次ノズルへの流体連通を提供する前記ダイバータバルブの第2の位置を決定する、請求項10に記載の航空機ターボファンエンジン(10)。
- 前記アクティブダイバータバルブが、エンジンFADECと通信状態にある、請求項8に記載の航空機ターボファンエンジン(10)。
- 前記エンジンFADECが、前記エンジンの作動条件に基づいて前記アクティブダイバータバルブの位置を決定する、請求項13に記載の航空機ターボファンエンジン(10)。
- 前記第3の空気ダクトにおける前記第3のストリーム空気流の圧力が、前記バイパス空気ストリーム流れの圧力よりも低い圧力である、請求項1に記載の航空機ターボファンエンジン(10)。
- 前記第3の空気ダクトに提供される第3のストリーム空気が、前記バイパス空気ストリームの前方で前記エンジンのファン部分から抽気される、請求項1に記載の航空機ターボファンエンジン(10)。
- 前記第3のストリーム空気が、ブレードオンファン又はFLADE(商標)によって前記第3の空気ダクトに提供され、前記第3の空気ダクトにおける前記第3のストリーム空気が、前記コア空気流及びバイパス空気ストリーム流れからシールされている、請求項1に記載の航空機ターボファンエンジン(10)。
- 前記流れダイバータバルブが、前記1次ノズルの断面A7にわたって前記1次ノズルに隣接した前記第3の空気ダクト内に配置される、請求項1に記載の航空機ターボファンエンジン(10)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/888,967 | 2013-05-07 | ||
US13/888,967 US9920710B2 (en) | 2013-05-07 | 2013-05-07 | Multi-nozzle flow diverter for jet engine |
PCT/US2014/035497 WO2015012919A2 (en) | 2013-05-07 | 2014-04-25 | Multi-nozzle flow diverter for jet engine |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2016517927A true JP2016517927A (ja) | 2016-06-20 |
JP6471148B2 JP6471148B2 (ja) | 2019-02-13 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2016512928A Expired - Fee Related JP6471148B2 (ja) | 2013-05-07 | 2014-04-25 | ジェットエンジン用の複数ノズル分流器 |
Country Status (7)
Country | Link |
---|---|
US (1) | US9920710B2 (ja) |
EP (1) | EP2994632A2 (ja) |
JP (1) | JP6471148B2 (ja) |
CN (1) | CN105190005B (ja) |
BR (1) | BR112015026459A2 (ja) |
CA (1) | CA2910960A1 (ja) |
WO (1) | WO2015012919A2 (ja) |
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- 2014-04-25 CN CN201480025760.6A patent/CN105190005B/zh active Active
- 2014-04-25 WO PCT/US2014/035497 patent/WO2015012919A2/en active Application Filing
- 2014-04-25 BR BR112015026459A patent/BR112015026459A2/pt not_active Application Discontinuation
- 2014-04-25 JP JP2016512928A patent/JP6471148B2/ja not_active Expired - Fee Related
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Also Published As
Publication number | Publication date |
---|---|
WO2015012919A2 (en) | 2015-01-29 |
CN105190005B (zh) | 2017-10-31 |
CN105190005A (zh) | 2015-12-23 |
CA2910960A1 (en) | 2015-01-29 |
EP2994632A2 (en) | 2016-03-16 |
WO2015012919A3 (en) | 2015-03-26 |
US20140345253A1 (en) | 2014-11-27 |
BR112015026459A2 (pt) | 2017-07-25 |
US9920710B2 (en) | 2018-03-20 |
JP6471148B2 (ja) | 2019-02-13 |
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