JP2004084669A5 - - Google Patents

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Publication number
JP2004084669A5
JP2004084669A5 JP2003302330A JP2003302330A JP2004084669A5 JP 2004084669 A5 JP2004084669 A5 JP 2004084669A5 JP 2003302330 A JP2003302330 A JP 2003302330A JP 2003302330 A JP2003302330 A JP 2003302330A JP 2004084669 A5 JP2004084669 A5 JP 2004084669A5
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JP
Japan
Prior art keywords
flow
region
air flow
intake
air
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.)
Pending
Application number
JP2003302330A
Other languages
English (en)
Japanese (ja)
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JP2004084669A (ja
Filing date
Publication date
Priority claimed from US10/064,884 external-priority patent/US6655632B1/en
Application filed filed Critical
Publication of JP2004084669A publication Critical patent/JP2004084669A/ja
Publication of JP2004084669A5 publication Critical patent/JP2004084669A5/ja
Pending legal-status Critical Current

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JP2003302330A 2002-08-27 2003-08-27 航空機用エンジンの吸気部領域の有効貫流面積を能動的に変化させるためのシステム及び方法 Pending JP2004084669A (ja)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/064,884 US6655632B1 (en) 2002-08-27 2002-08-27 System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine

Publications (2)

Publication Number Publication Date
JP2004084669A JP2004084669A (ja) 2004-03-18
JP2004084669A5 true JP2004084669A5 (enExample) 2006-10-05

Family

ID=29547861

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2003302330A Pending JP2004084669A (ja) 2002-08-27 2003-08-27 航空機用エンジンの吸気部領域の有効貫流面積を能動的に変化させるためのシステム及び方法

Country Status (4)

Country Link
US (1) US6655632B1 (enExample)
EP (1) EP1394388A3 (enExample)
JP (1) JP2004084669A (enExample)
BR (1) BR0303430B1 (enExample)

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US9228534B2 (en) * 2007-07-02 2016-01-05 United Technologies Corporation Variable contour nacelle assembly for a gas turbine engine
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US9884688B2 (en) 2013-02-14 2018-02-06 Gulfstream Aerospace Corporation Propulsion system using large scale vortex generators for flow redistribution and supersonic aircraft equipped with the propulsion system
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US10378554B2 (en) 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
US10145301B2 (en) 2014-09-23 2018-12-04 Pratt & Whitney Canada Corp. Gas turbine engine inlet
US9957807B2 (en) 2015-04-23 2018-05-01 Pratt & Whitney Canada Corp. Rotor assembly with scoop
US9938848B2 (en) 2015-04-23 2018-04-10 Pratt & Whitney Canada Corp. Rotor assembly with wear member
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US10487744B2 (en) * 2016-05-23 2019-11-26 United Technologies Corporation Fence for duct tone mitigation
US10787254B1 (en) * 2016-10-21 2020-09-29 Franklin Y. K. Chen VTOL flying taxicab
US10724540B2 (en) 2016-12-06 2020-07-28 Pratt & Whitney Canada Corp. Stator for a gas turbine engine fan
US10690146B2 (en) 2017-01-05 2020-06-23 Pratt & Whitney Canada Corp. Turbofan nacelle assembly with flow disruptor
EP3412563B1 (en) * 2017-06-08 2022-11-23 Airbus Defence and Space GmbH Variable and adaptable diverterless bump inlet
US10436112B2 (en) 2017-06-26 2019-10-08 The Boeing Company Translating turning vanes for a nacelle inlet
FR3095194B1 (fr) * 2019-04-17 2021-08-13 Safran Aircraft Engines Entrée d’air de nacelle de turboréacteur comprenant un dispositif de déviation pour favoriser une phase d’inversion de poussée
US11993389B2 (en) * 2020-12-11 2024-05-28 Rohr, Inc. Aircraft propulsion system inlet structure with variable airflow inlet area
US11767790B2 (en) 2021-08-23 2023-09-26 General Electric Company Object direction mechanism for turbofan engine
US11739689B2 (en) 2021-08-23 2023-08-29 General Electric Company Ice reduction mechanism for turbofan engine
US12385430B2 (en) 2023-11-30 2025-08-12 General Electric Company Gas turbine engine with forward swept outlet guide vanes
US12209557B1 (en) 2023-11-30 2025-01-28 General Electric Company Gas turbine engine with forward swept outlet guide vanes
US12228037B1 (en) 2023-12-04 2025-02-18 General Electric Company Guide vane assembly with fixed and variable pitch inlet guide vanes
US12313021B1 (en) 2024-03-14 2025-05-27 General Electric Company Outer nacelle with inlet guide vanes and acoustic treatment
US12397922B1 (en) * 2024-05-10 2025-08-26 The Boeing Company Engine nacelle inlet having a turbulator segment

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