JP2008144764A - 航空機エンジンノズルの流体のパッシブ誘導システムおよび方法 - Google Patents
航空機エンジンノズルの流体のパッシブ誘導システムおよび方法 Download PDFInfo
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- 239000012530 fluid Substances 0.000 title claims abstract description 234
- 238000000034 method Methods 0.000 title claims description 20
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- 239000012080 ambient air Substances 0.000 claims abstract description 13
- 238000011144 upstream manufacturing Methods 0.000 claims description 9
- 230000006698 induction Effects 0.000 claims 5
- 230000009969 flowable effect Effects 0.000 claims 1
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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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
- F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
- F02K1/30—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for varying effective area of jet pipe or nozzle
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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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
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- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/13—Two-dimensional trapezoidal
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- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/17—Purpose of the control system to control boundary layer
- F05D2270/173—Purpose of the control system to control boundary layer by the Coanda effect
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- 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】航空機のターボファンエンジンに取付け可能な航空機ノズルを含み、そのノズルはエンジンの排気生成物を流す第1の流体路222を囲む第1の流体路壁221と、エンジンのバイパス空気を流す第2の流体路224を囲む第2の流体路壁223とを備えている。第1の流体路壁221は第1と第2の流体路の間に配置され、第2の流体路壁223は第2の流体路と周囲空気流路との間に配置されている。多数の流体通路は流体路壁に対して外部の対応する流体路に流体路壁を通る流体路壁内の対応する流体路から受動的にガスを導くように配置される。隣接する流体通路は隣接して円周方向に間隔を隔てて設けられ、出口開口は流体路壁の外部の対応する流体路と境界を接して配置されている。
【選択図】図3
Description
Claims (16)
- 航空機のターボファンエンジンに取付け可能な航空機ノズルを具備し、
そのノズルは、第1の流体路を囲み、エンジン排気生成物を受けるように配置されている第1の流体路壁と、
第2の流体路を囲み、エンジンのバイパス空気を受けるように配置されている第2の流体路壁と、
第1と第2の流体路壁の少くなくも1つに設けられている多数の流体通路とを備え、
第1の流体路壁は第1と第2の流体路の間に位置し、第2の流体路壁は第2の流体路と周囲空気流の流体路との間に位置し、
前記多数の流体通路は、流体路壁の内側の流体路から流体路壁の外側の対応する流体路に流体路壁を通ってパッシブにガスを導くように配置され、隣接する流体通路は円周方向で隣接して間隔を隔てて設けられた出口開口を前記流体路壁の外側の対応する流体路との境界に設けられている航空機システム。 - 前記流体路はガスを後方に導くような形状である請求項1記載のシステム。
- 前記流体路壁内の対応する流体路は後端で終端しており、それは離れた後方の突出部を含んでいない請求項1記載のシステム。
- 個々の出口開口はその出口開口に対応する閉鎖装置を有し、システムはさらに出口開口を開閉するように閉鎖装置に結合されて動作するアクチュエータを備えている請求項1記載のシステム。
- さらに、エンジンの状態と飛行状態の少なくとも一方に対応する入力信号を送信するように構成された入力装置と、
アクチュエータと入力装置とに結合されて入力信号を受信し、入力信号に少なくとも部分的に基づいてアクチュエータの動作を命令する制御装置とを備えている請求項4記載のシステム。 - 出口開口は第1の流体路壁中に設けられている請求項1記載のシステム。
- 出口開口は第2の流体路壁の後部エッジの後方に位置する請求項6記載のシステム。
- 出口開口は第2の流体路壁中に設けられている請求項1記載のシステム。
- さらに、個々の出口開口と連結されて流体を流通させて出口開口において個々の出口開口を開閉するように動作する閉鎖装置と、
その閉鎖装置に結合されて、閉鎖装置の動作を指令する制御装置とを備え、航空機ノズルは出口開口が閉じられたとき第1の出口面積を有し、出口開口が開かれたとき第1の出口面積よりも大きい第2の出口面積を有している請求項8記載のシステム。 - 個々の流体通路は、対応する出口開口の上流の隣接する流体路に対しては流通可能ではない請求項9記載のシステム。
- 航空機ターボファンエンジンからの排気ガス生成物を対応するエンジンノズルの第1の流体路に沿って導き、
エンジンの周囲にエンジンノズルの第2の流体路に沿ってバイパス空気を導き、
(a)円周方向の断続した位置において第1の流体路から第2の流体路にパッシブにガスを導き、または(b)断続的に円周方向に沿って間隔を隔てられた位置において第2の流体路から周囲の空気流へガスを導き、または(c)前記(a)および(b)の両方の流体路からガスを導く航空機エンジンの動作方法。 - パッシブなガスの誘導においては、(a)第1の流体路、(b)第2の流体路、または(c)前記(a)および(b)の両流体路から除去された後のガスに対してエネルギを付加することなくガスを導く請求項11記載の方法。
- パッシブなガスの誘導は、エンジンノズルにより支持されているシェブロンの使用なしで行なわれるガスと周囲空気流との混合を含んでいる請求項11記載の方法。
- パッシブなガス誘導は、第1の流体路、第2の流体路、または第1、第2の両流体路の出口におけるシェブロンの存在により生じる流体混合を少なくとも部分的にエミュレートしている請求項11記載の方法。
- 第2の流体路から周囲空気流へのパッシブなガス誘導は、周囲空気流の速度よりも大きくバイパス空気流の速度よりも小さい速度を有するガスを導く請求項11記載の方法。
- パッシブなガスの誘導は、周囲空気流との境界に位置している円周方向で間隔を隔てられた複数の出口開口を通って第2の流体路からガスを導き、さらに、バイパス空気に対して実効出口面積を減少させるように境界部において出口開口を選択的に閉じ、エンジンによって生成される推力と周囲空気流の状態に対応するように出口開口を選択的に再度開放する請求項11記載の方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/635,737 US7870722B2 (en) | 2006-12-06 | 2006-12-06 | Systems and methods for passively directing aircraft engine nozzle flows |
US11/635,737 | 2006-12-06 |
Publications (3)
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JP2008144764A true JP2008144764A (ja) | 2008-06-26 |
JP2008144764A5 JP2008144764A5 (ja) | 2011-01-27 |
JP5241215B2 JP5241215B2 (ja) | 2013-07-17 |
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JP2007315963A Expired - Fee Related JP5241215B2 (ja) | 2006-12-06 | 2007-12-06 | 航空機エンジンノズルの流体のパッシブ誘導システムおよび方法 |
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US (2) | US7870722B2 (ja) |
EP (1) | EP1936172B1 (ja) |
JP (1) | JP5241215B2 (ja) |
CN (1) | CN101200220B (ja) |
ES (1) | ES2391115T3 (ja) |
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WO2021009953A1 (ja) * | 2019-07-12 | 2021-01-21 | 三菱重工業株式会社 | ガスタービンシステムおよびそれを備えた移動体 |
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Also Published As
Publication number | Publication date |
---|---|
US7870722B2 (en) | 2011-01-18 |
JP5241215B2 (ja) | 2013-07-17 |
CN101200220A (zh) | 2008-06-18 |
ES2391115T3 (es) | 2012-11-21 |
EP1936172B1 (en) | 2012-07-11 |
CN101200220B (zh) | 2013-08-14 |
US20110072781A1 (en) | 2011-03-31 |
US20080134665A1 (en) | 2008-06-12 |
US8166768B2 (en) | 2012-05-01 |
EP1936172A2 (en) | 2008-06-25 |
EP1936172A3 (en) | 2010-04-21 |
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