WO2012156828A1 - Réduction du frottement par insufflation d'air dans la couche limite d'écoulement du fuselage d'aéronef - Google Patents

Réduction du frottement par insufflation d'air dans la couche limite d'écoulement du fuselage d'aéronef Download PDF

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Publication number
WO2012156828A1
WO2012156828A1 PCT/IB2012/050263 IB2012050263W WO2012156828A1 WO 2012156828 A1 WO2012156828 A1 WO 2012156828A1 IB 2012050263 W IB2012050263 W IB 2012050263W WO 2012156828 A1 WO2012156828 A1 WO 2012156828A1
Authority
WO
WIPO (PCT)
Prior art keywords
boundary layer
hot gas
flow
temperature
increase
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.)
Ceased
Application number
PCT/IB2012/050263
Other languages
German (de)
English (en)
Inventor
Sebastian Kortz
Klaus Braeutigam
Johannes LEBERT
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of WO2012156828A1 publication Critical patent/WO2012156828A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
    • 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
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
    • 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

Definitions

  • Frictional resistance component such as the delay of the laminar-turbulent handling, influencing the turbulence component by so-called "riblets” or boundary layer exhaustion Kramer et al. [1] investigated in wind tunnel and flight tests the possibility of frictional resistance by heating the boundary layer by heating the surface around.
  • riblets boundary layer exhaustion Kramer et al.
  • Hot gas may be a gas of the same nature as the flow medium (air) but with the essential one
  • the exhaust air of the heat exchanger can be used, with the e.g. on the B747-400 and other aircraft models, the hot engine bleed air is cooled down by approximately 50 ° using a small portion of the exhaust air from the engine's secondary flow (Fan Air).
  • the thus heated exhaust air of the heat exchanger is introduced by means of a suitable piping system through the engine nacelle and then in the field of rempligelvorder- or hinterholms to the fuselage. From there, the hot gas at a suitable location is either singular or, if more effective, at several sections of the
  • the essentially new of the invention is thus the method, the boundary layer temperature through
  • This method has the advantage that it prevents the extreme convective heat transfer from the surface to the flow by means of the hot gas film, and at the same time heats the boundary layer.
  • the prior art does not make it possible to increase the boundary layer temperature of a commercial aircraft at high Reynolds numbers so that a significant influence on the frictional resistance occurs.
  • the invention described above has the advantage that it prevents the extreme convective heat transfer from the surface to the flow by means of the hot gas film, and at the same time heats the boundary layer, so that the heating of the wall (aircraft outer skin) is eliminated.
  • the invention has not yet been tested.
  • a model test is planned.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Le réchauffement de la couche limite s'avère un moyen efficace de réduire la proportion de résistance au frottement turbulent quand les nombres de Reynolds sont bas. Quand les nombres de Reynolds sont élevés comme c'est le cas pour les avions de ligne, la diminution de la proportion de résistance au frottement turbulent est toutefois marginale parce que la puissance de chauffage électrique nécessaire ne peut pas être fournie en raison de la forte transmission de chaleur par convection en essai de vol. Selon la présente invention, du gaz chaud est insufflé dans la couche limite d'écoulement du fuselage d'aéronef au lieu de chauffer la surface d'écoulement. Le gaz chaud peut être un gaz de même nature que le fluide d'écoulement (air) mais ayant la propriété essentielle que sa température est tellement supérieure à la température du fluide d'écoulement que la résistance au frottement est réduite. Le gaz chaud est prélevé dans l'air de prélèvement de la turbine par l'intermédiaire d'un échangeur de chaleur.
PCT/IB2012/050263 2011-05-14 2012-01-19 Réduction du frottement par insufflation d'air dans la couche limite d'écoulement du fuselage d'aéronef Ceased WO2012156828A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE202011100733.6 2011-05-14
DE202011100733U DE202011100733U1 (de) 2011-05-14 2011-05-14 Verminderung des Reibungswiderstands durch Einblasen von Heißgas in die Strömungsgrenzschicht des Flugzeugrumpfs

Publications (1)

Publication Number Publication Date
WO2012156828A1 true WO2012156828A1 (fr) 2012-11-22

Family

ID=44317594

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2012/050263 Ceased WO2012156828A1 (fr) 2011-05-14 2012-01-19 Réduction du frottement par insufflation d'air dans la couche limite d'écoulement du fuselage d'aéronef

Country Status (2)

Country Link
DE (1) DE202011100733U1 (fr)
WO (1) WO2012156828A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115371944A (zh) * 2022-07-22 2022-11-22 中国航空工业集团公司哈尔滨空气动力研究所 一种风洞试验转捩带附加阻力修正方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10174665B2 (en) 2016-03-18 2019-01-08 Pratt & Whitney Canada Corp. Active control flow system and method of cooling and providing active flow control

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959377A (en) * 1957-03-15 1960-11-08 Poly Ind Inc Airfoil structure with boundary layer control means
DE1506580A1 (de) * 1967-06-20 1969-09-04 Dornier Gmbh Steuerbarer Luftausblasespalt an Flugzeugtragflaechen
DE3339866A1 (de) * 1983-11-04 1985-05-15 Rähmer, Hans, 6100 Darmstadt Erhoehung des komplexwirkungsgrades von fahrzeugen
EP0230684A1 (fr) * 1985-12-30 1987-08-05 The Boeing Company Bec mobile de bord d'attaque, dispositif de dégivrage pour aile
EP0436243A2 (fr) * 1989-12-29 1991-07-10 The Boeing Company Dégivreur pour aéronefs

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959377A (en) * 1957-03-15 1960-11-08 Poly Ind Inc Airfoil structure with boundary layer control means
DE1506580A1 (de) * 1967-06-20 1969-09-04 Dornier Gmbh Steuerbarer Luftausblasespalt an Flugzeugtragflaechen
DE3339866A1 (de) * 1983-11-04 1985-05-15 Rähmer, Hans, 6100 Darmstadt Erhoehung des komplexwirkungsgrades von fahrzeugen
EP0230684A1 (fr) * 1985-12-30 1987-08-05 The Boeing Company Bec mobile de bord d'attaque, dispositif de dégivrage pour aile
EP0436243A2 (fr) * 1989-12-29 1991-07-10 The Boeing Company Dégivreur pour aéronefs

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115371944A (zh) * 2022-07-22 2022-11-22 中国航空工业集团公司哈尔滨空气动力研究所 一种风洞试验转捩带附加阻力修正方法

Also Published As

Publication number Publication date
DE202011100733U1 (de) 2011-06-29

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