Apparatus and methods to lower peak temperatures and improve performance of aircraft (100) anti-icing systems (200) are described herein. One described example apparatus includes a skin (206) on an inlet side of a nacelle (201) of an aircraft defining an annular chamber (211), a gas delivery system (212) disposed within the annular chamber to provide a first gas to mix with and entrain a second gas in the annular chamber to define a flow through the annular chamber, and a deflector vane (214) disposed within the annular chamber to redirect the flow through the annular chamber. The second gas is at a different temperature from the first gas.
Aircraft anti-icing systems having deflector vanes
Systeme zur Verhinderung der Flugzeugvereisung mit Umlenkschaufeln
Systèmes antigivrage d'avion comportant des aubes déflectrices
2019-11-06
Patent
Elektronische Ressource
Englisch