BRPI0510727A - arranjo de sucção de camada de contorno - Google Patents

arranjo de sucção de camada de contorno

Info

Publication number
BRPI0510727A
BRPI0510727A BRPI0510727-0A BRPI0510727A BRPI0510727A BR PI0510727 A BRPI0510727 A BR PI0510727A BR PI0510727 A BRPI0510727 A BR PI0510727A BR PI0510727 A BRPI0510727 A BR PI0510727A
Authority
BR
Brazil
Prior art keywords
contour layer
suction arrangement
suction
contour
layer suction
Prior art date
Application number
BRPI0510727-0A
Other languages
English (en)
Inventor
Juergen Meister
Juergen Pfenning
Original Assignee
Airbus Gmbh
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Airbus Gmbh filed Critical Airbus Gmbh
Publication of BRPI0510727A publication Critical patent/BRPI0510727A/pt

Links

Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/08—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid Mechanics (AREA)
  • Physics & Mathematics (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Fats And Perfumes (AREA)
  • Medicines Containing Material From Animals Or Micro-Organisms (AREA)

Abstract

ARRANJO DE SUCçãO DE CAMADA DE CONTORNO. A invenção diz respeito a um arranjo de sucção para extrair camadas de contorno em uma aeronave com uma estrutura, cuja pele externa contém superfícies de sucção em áreas de fluxo críticas, e com pelo menos um motor atmosférico. Ar de sangria é extraído da região de alta pressão (P) do motor (1) por meio de uma linha de derivação (10) e usado para acionar a turbina (20) de um conjunto turbo supercarregador (2), cujo compressor (24) serve como uma fonte de sucção para extrair a camada de contorno.
BRPI0510727-0A 2004-05-13 2005-05-11 arranjo de sucção de camada de contorno BRPI0510727A (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102004024016A DE102004024016A1 (de) 2004-05-13 2004-05-13 Anordnung zur Grenzschichtabsaugung
US60664904P 2004-09-02 2004-09-02
PCT/EP2005/005098 WO2005113335A1 (en) 2004-05-13 2005-05-11 Boundary layer suction arrangement

Publications (1)

Publication Number Publication Date
BRPI0510727A true BRPI0510727A (pt) 2007-11-20

Family

ID=35432964

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0510727-0A BRPI0510727A (pt) 2004-05-13 2005-05-11 arranjo de sucção de camada de contorno

Country Status (10)

Country Link
US (1) US7837155B2 (pt)
EP (1) EP1744953B1 (pt)
JP (1) JP4786647B2 (pt)
CN (1) CN1950255B (pt)
AT (1) ATE482140T1 (pt)
BR (1) BRPI0510727A (pt)
CA (1) CA2565011C (pt)
DE (2) DE102004024016A1 (pt)
RU (1) RU2384466C2 (pt)
WO (1) WO2005113335A1 (pt)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2074323B1 (en) * 2006-10-12 2012-11-21 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
DE102009043489A1 (de) 2009-09-30 2011-03-31 Airbus Operations Gmbh Vorrichtung zur Grenzschichtabsaugung und Verbundbauteil hierfür
US9630706B2 (en) * 2013-02-22 2017-04-25 Rolls-Royce Corporation Positionable ejector member for ejector enhanced boundary layer alleviation
RU2534480C1 (ru) * 2013-06-26 2014-11-27 Виктор Семенович Савченков Способ увеличения подъёмной силы крыла самолёта
US9789954B2 (en) * 2014-04-25 2017-10-17 Rohr, Inc. Method of controlling boundary layer flow
CN109367796B (zh) * 2018-09-17 2022-03-15 江西洪都航空工业集团有限责任公司 一种基于流体震荡器的埋入式进气道附面层控制装置
CN110374747A (zh) * 2019-07-25 2019-10-25 中国航发沈阳发动机研究所 一种具有自补偿功能的飞机发动机引气管路

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2833492A (en) * 1955-02-07 1958-05-06 Harlan D Fowler Boundary layer control system with aerodynamic glove
GB1443333A (en) * 1972-08-12 1976-07-21 Mtu Muenchen Gmbh Aircraft having apparatus for augmenting the lift of the aircraft
DE3412101A1 (de) 1984-03-31 1985-10-10 Deutsche Airbus GmbH, 8000 München Einbauanordnung eines hilfstriebwerkes im rumpfheck von transportflugzeugen zur wirtschaftlichen erzeugung von klimaluft und von vortriebsschub im flug
US5114103A (en) 1990-08-27 1992-05-19 General Electric Company Aircraft engine electrically powered boundary layer bleed system
RU2028963C1 (ru) 1990-10-02 1995-02-20 Гришин Александр Николаевич Летательный аппарат с системой ламинаризации обтекания
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
RU2084377C1 (ru) 1992-11-02 1997-07-20 Александр Николаевич Гришин Силовая установка летательного аппарата с системой ламинаризации обтекания аэродинамических поверхностей
GB9400555D0 (en) * 1994-01-13 1994-03-09 Short Brothers Plc Boundery layer control in aerodynamic low drag structures
US5779196A (en) 1995-12-08 1998-07-14 The Boeing Company Ram air drive laminar flow control system
DE19617952C2 (de) 1996-05-04 1998-07-02 Daimler Benz Aerospace Airbus Absauggeneratorsystem eines Flugzeuges für die Laminarhaltung der Grenzschicht
DE19643069C2 (de) * 1996-10-18 1999-03-25 Daimler Benz Aerospace Airbus Seitenleitwerksstrukur für ein Flugzeug
DE19820097C2 (de) * 1998-05-06 2003-02-13 Airbus Gmbh Anordnung zur Grenzschichtabsaugung und Stoßgrenzschichtkontrolle für ein Flugzeug
US6189324B1 (en) 1999-10-05 2001-02-20 Samuel B. Williams Environment control unit for turbine engine

Also Published As

Publication number Publication date
CN1950255A (zh) 2007-04-18
DE102004024016A1 (de) 2005-12-22
JP2007537085A (ja) 2007-12-20
EP1744953A1 (en) 2007-01-24
CA2565011A1 (en) 2005-12-01
CN1950255B (zh) 2011-05-18
ATE482140T1 (de) 2010-10-15
WO2005113335A1 (en) 2005-12-01
DE602005023724D1 (de) 2010-11-04
RU2006143163A (ru) 2008-06-20
US7837155B2 (en) 2010-11-23
EP1744953B1 (en) 2010-09-22
JP4786647B2 (ja) 2011-10-05
CA2565011C (en) 2013-04-16
RU2384466C2 (ru) 2010-03-20
US20070266707A1 (en) 2007-11-22

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Legal Events

Date Code Title Description
B25D Requested change of name of applicant approved

Owner name: AIRBUS OPERATIONS GMBH (DE)

Free format text: NOME ALTERADO DE: AIRBUS DEUTSCHLAND GMBH

B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]
B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]