An apparatus for improving heat transfer through a leading portion of an aircraft engine. The apparatus includes a wall that is defined by the leading portion. A surface is defined by the wall and the surface defines a channel through the leading portion of the aircraft engine. A source for a fluid that is fluidly connected to the channel. Pits are defined in the surface of the channel such that the bleed air can flow across the pits.
DIMPLED NACELLE INNER-SURFACE FOR HEAT TRANSFER IMPROVEMENT
SURFACE INTERIEURE DE NACELLE A BOSSETTES DESTINEE A L'AMELIORATION DU TRANSFERT THERMIQUE
2017-11-02
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F15D FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS , Strömungsdynamik, d.h. Verfahren oder Vorrichtungen zum Beeinflussen der Strömung von Gasen oder Flüssigkeiten |
DIMPLED NACELLE INNER-SURFACE FOR HEAT TRANSFER IMPROVEMENT
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