Aircraft anti-icing systems having deflector vanes
First Claim
Patent Images
1. An apparatus comprising:
- a skin on an inlet side of a nacelle of an aircraft defining an annular chamber;
a gas delivery system including a nozzle disposed within the annular chamber, the nozzle 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, wherein the second gas is at a different temperature from the first gas; and
a deflector vane disposed within the annular chamber and in a direct impingement flow path of the nozzle, the deflector vane to redirect the flow through the annular chamber to increase a flow path length of the flow through the annular chamber.
1 Assignment
0 Petitions
Accused Products
Abstract
Apparatus and methods to lower peak temperatures and improve performance of aircraft anti-icing systems are described herein. One described example apparatus includes a skin on an inlet side of a nacelle of an aircraft defining an annular chamber, a gas delivery system 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 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.
-
Citations
21 Claims
-
1. An apparatus comprising:
-
a skin on an inlet side of a nacelle of an aircraft defining an annular chamber; a gas delivery system including a nozzle disposed within the annular chamber, the nozzle 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, wherein the second gas is at a different temperature from the first gas; and a deflector vane disposed within the annular chamber and in a direct impingement flow path of the nozzle, the deflector vane to redirect the flow through the annular chamber to increase a flow path length of the flow through the annular chamber. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
-
-
10. An apparatus comprising:
-
a chamber in an outboard structure of an aircraft, the chamber on a fore side of the outboard structure; a gas delivery system including a nozzle disposed within the chamber having an outlet to provide a gas to the chamber, the gas to define a flow through the chamber; and a deflector vane disposed in a direct impingement flow path of the nozzle, wherein the deflector vane is to redirect the flow through the chamber to increase a flow path length of the flow by causing the flow to impinge the deflector vane prior to impinging an inner surface of the chamber. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17)
-
-
18. A method comprising:
-
receiving a gas into a chamber of an aircraft, the gas to define a flow from a nozzle into the chamber in a first flow path direction; and impinging the flow onto a vane that is in a direct impingement flow path relative to the nozzle to re-direct the flow in a second flow path direction within the chamber to increase a flow path length of the flow. - View Dependent Claims (19, 20, 21)
-
Specification