JP2004084669A - 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 - Google Patents

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 Download PDF

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Publication number
JP2004084669A
JP2004084669A JP2003302330A JP2003302330A JP2004084669A JP 2004084669 A JP2004084669 A JP 2004084669A JP 2003302330 A JP2003302330 A JP 2003302330A JP 2003302330 A JP2003302330 A JP 2003302330A JP 2004084669 A JP2004084669 A JP 2004084669A
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Japan
Prior art keywords
area
flow
intake
parter
suction
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
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JP2003302330A
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English (en)
Japanese (ja)
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JP2004084669A5 (enExample
Inventor
Anurag Gupta
アヌラーグ・グプタ
Paolo Graziosi
パオロ・グラツィオーシ
Ramani Mani
ラマニ・マニ
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
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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    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • 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
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • Y02T50/10—Drag 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)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
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 true JP2004084669A (ja) 2004-03-18
JP2004084669A5 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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JP2008298067A (ja) * 2007-05-29 2008-12-11 United Technol Corp <Utc> ナセルの入口流制御システム、ガスタービンエンジンのナセルおよびその内側表面からの空気流の剥離を防ぐ方法
JP2008309152A (ja) * 2007-06-13 2008-12-25 United Technol Corp <Utc> ナセルアッセンブリ、ガスタービンエンジンおよびナセルの入口縁部の有効境界層厚さを大きくする方法

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US8408491B2 (en) * 2007-04-24 2013-04-02 United Technologies Corporation Nacelle assembly having inlet airfoil for a gas turbine engine
US8205430B2 (en) * 2007-05-16 2012-06-26 United Technologies Corporation Variable geometry nacelle assembly for a gas turbine engine
US8727267B2 (en) * 2007-05-18 2014-05-20 United Technologies Corporation Variable contraction ratio nacelle assembly for a gas turbine engine
US20080308684A1 (en) * 2007-06-15 2008-12-18 Chaudhry Zaffir A Nacelle with articulating leading edge slates
US8402739B2 (en) 2007-06-28 2013-03-26 United Technologies Corporation Variable shape inlet section for a nacelle assembly of a gas turbine engine
US9228534B2 (en) * 2007-07-02 2016-01-05 United Technologies Corporation Variable contour nacelle assembly for a gas turbine engine
US20090064684A1 (en) * 2007-07-13 2009-03-12 United Technologies Corp. Systems Involving Inlet-Mounted Engine Controls
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EP2180164A1 (en) * 2008-10-23 2010-04-28 Mbda Uk Limited Method and system for altering engine air intake geometry
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US10145301B2 (en) 2014-09-23 2018-12-04 Pratt & Whitney Canada Corp. Gas turbine engine inlet
US10378554B2 (en) 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
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
FR3048727B1 (fr) * 2016-03-14 2018-03-02 Safran Aircraft Engines Conduit d'entree d'air pour une turbomachine d'aeronef
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
US12209557B1 (en) 2023-11-30 2025-01-28 General Electric Company Gas turbine engine with forward swept outlet guide vanes
US12385430B2 (en) 2023-11-30 2025-08-12 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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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008298067A (ja) * 2007-05-29 2008-12-11 United Technol Corp <Utc> ナセルの入口流制御システム、ガスタービンエンジンのナセルおよびその内側表面からの空気流の剥離を防ぐ方法
JP2008309152A (ja) * 2007-06-13 2008-12-25 United Technol Corp <Utc> ナセルアッセンブリ、ガスタービンエンジンおよびナセルの入口縁部の有効境界層厚さを大きくする方法

Also Published As

Publication number Publication date
BR0303430B1 (pt) 2012-06-12
EP1394388A3 (en) 2006-07-05
EP1394388A2 (en) 2004-03-03
US6655632B1 (en) 2003-12-02
BR0303430A (pt) 2004-09-08

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