Airfoil anti-icing assembly and method

• US 6,702,233 B1
• Filed: 02/07/2001
• Issued: 03/09/2004
• Est. Priority Date: 02/07/2001
• Status: Expired due to Term

• Current Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: DuPont, Henry Morgan
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US09/778,178
• Time in Patent Office: 1,126 Days
• Field of Search: 244/134.B, 244/134.R, 60/390.93
• US Class Current: 244/134.00B
• CPC Class Codes: B64D 15/04 Hot gas application

Abstract

An anti-icing assembly for an airfoil such as an aircraft wing or slat comprises: (a) an airfoil having an exterior surface and interior wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity; (b) an inlet plenum integral to the airfoil, wherein the inlet plenum comprises (i) an inlet baffle capable of directing hot gases into the airfoil interior cavity and (ii) a throat section interfacing the inlet plenum and airfoil interior cavity; and (c) an outlet plenum integral to the airfoil, wherein the outlet plenum comprises an outlet baffle capable of directing hot gases from the airfoil interior cavity. The airfoil anti-icing method of this invention comprises providing hot gases such as jet engine bleed air to the airfoil assembly of this invention, swirling the hot gases within the airfoil interior cavity, and discharging the hot gases from the airfoil interior cavity through the airfoil outlet end. The system of this invention comprises a source of hot gases, typically jet engine bleed air, and the airfoil assembly of this invention.

Claims

1. An anti-icing assembly for an aircraft wing or wing slat comprising:

(a) an aircraft wing or wing slat having an exterior surface, an interior surface and a plenum wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity;

(b) an inlet plenum integral to the aircraft wing or wing slat, wherein the inlet plenum comprises (i) an inlet baffle capable of directing hot gases into the interior cavity and (ii) a throat section interfacing the inlet plenum and interior cavity;

said plenum wall is located adjacent to said inlet plenum and

(c) an outlet plenum integral to the aircraft wing or wing slat, wherein the outlet plenum is located within the same interior cavity as the inlet plenum, and the outlet plenum comprises an outlet baffle capable of directing hot gases from the interior cavity through an outlet end away from the wing or wing slat.

2. The assembly of claim 1, in which the hot gases swirl within the airfoil interior cavity.

3. The assembly of claim 1, in which the hot gases entering the airfoil interior cavity from the inlet plenum form a wall jet.

4. The assembly of claim 1, in which the outlet plenum is located at the bottom portion of the airfoil.

5. The assembly of claim 1, in which the outlet plenum is located at the side portion of the airfoil.

6. The assembly of claim 1, in which the outlet plenum is located at the middle portion of the airfoil.

7. The assembly of claim 1, in which the throat section of the inlet plenum is slot-shaped.

8. The assembly of claim 1, in which the hot gases are obtained from jet engine bleed air.

16. The method of claim 8, in which the hot gases are obtained from jet engine bleed air.

9. An aircraft wing or wing slat anti-icing method comprising:

(a) providing an, assembly comprising;

(i) an aircraft wing or wing slat having an exterior surface, an interior surface and a plenum wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity;

(ii) an inlet plenum integral to the aircraft wing or wing slat, wherein the inlet plenum comprises an inlet baffle capable of directing hot gases into the interior cavity and a throat section interfacing the inlet plenum and interior cavity;

said plenum wall is located adjacent to said inlet plenum and (iii) an outlet plenum integral to the aircraft wing or wing slat, wherein the outlet plenum is located within the same interior cavity as the inlet plenum, and tile outlet plenum comprises an outlet baffle capable of directing hot gases from the interior cavity through an outlet end cavity from the wing or wing slat;

(b) introducing hot gases into the inlet plenum; and

(c) discharging the hot gases from the interior cavity through the outlet and away from the wing or wing slat.

10. The method of claim 9, in which the hot gases swirl within the airfoil interior cavity.

11. The method of claim 10, In which the hot gases entering the airfoil interior cavity from the inlet plenum form a wall jet.

12. The method of claim 9, in which the outlet plenum is located at the bottom portion of the airfoil.

13. The method of claim 9, in which the outlet plenum is located at the side portion of the airfoil.

14. The method of claim 9, in which the outlet plenum is located at the middle portion of the airfoil.

15. The method of claim 9, in which the throat section of the inlet plenum is slot-shaped.

17. An anti-icing system for an aircraft wing or wing slat, the system comprising:

(a) a source of hot gases;

(b) an aircraft wing or wing slat having an exterior surface, an interior surface and a plenum wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity;

(c) an inlet plenum integral to the aircraft wing or wing slat, wherein the inlet plenum comprises (i) an inlet baffle capable of directing hot gases into the interior cavity and (ii) a throat section interfacing the inlet plenum and interior cavity;

said plenum wall is located adjacent to said inlet plenum and

(d) an outlet plenum integral to the aircraft wing or wing slat, wherein the outlet plenum is located within the same interior cavity as the inlet plenum, and the outlet plenum comprises an outlet baffle capable of directing hot gases from the interior cavity through a end away from the wing or wing salt.

18. An anti-icing assembly for an aircraft wing or wing slat comprising:

(a) an aircraft wing or wing slat having an exterior surface, an interior surface and a plenum wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity;

(b) an inlet plenum integral to the aircraft wing or wing slat, wherein the inlet plenum comprises (i) an inlet baffle capable of directing hot gases into the interior cavity such that the hot gases swirl within the interior cavity with a swirl factor ranging from about 0.1 to about 3.5 arid (ii) a throat section interfacing the inlet plenum and interior cavity;

said plenum wall is located adjacent to said inlet plenum and

(c) an outlet plenum integral to the aircraft wing or wing slat, wherein the outlet plenum is located within the same interior cavity as the inlet plenum, and the outlet plenum comprises an outlet baffle capable of directing hot gases from the interior cavity through an outlet end away from the wing or wing slat.

19. An aircraft wing or wing slat anti-icing method comprising:

(a) providing an assembly comprising;

(i) an aircraft wing or wing slat having an exterior surface, an interior surface and a plenum wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity;

(ii) an inlet plenum integral to the aircraft wing or wing slat, wherein the inlet plenum comprises an inlet baffle capable of directing hot gases into the interior cavity such that the hot vases swirl within the interior cavity with a swirl factor ranging from about 0.1 to about 3.5 and a throat section interfacing the inlet plenum and interior cavity;

said plenum wall is located adjacent to said inlet plenum and (iii) an outlet plenum integral to the aircraft wing or wing slat, wherein the outlet plenum is located within the same interior cavity as the inlet plenum, and the outlet plenum comprises an outlet baffle capable of directing hot gases from the interior cavity through an outlet end away from the wing or wing slat;

(b) introducing hot gases into the inlet plenum; and

(c) discharging the hot gases from the interior cavity through the outlet end away from the wing or wing slat.

20. An anti-icing system for an aircraft wing or wing slat, the system comprising:

(a) a source of hot gases;

(b) an aircraft wing or wing slat having an exterior surface, an interior surface and a plenum wall defining an interior cavity, and bottom, middle and side portions all adjacent to the interior cavity;

(c) an inlet plenum integral to the aircraft wing or wing slat, wherein the inlet plenum comprises (i) an inlet baffle capable of directing hot gases into the interior cavity such that the hot gases swirl within the interior cavity with a swirl factor ranging from about 0.1 to about 3.5 and (ii) a throat section interfacing the inlet plenum and interior cavity;

said plenum wall is located adjacent to said inlet plenum and

(d) an outlet plenum integral to the aircraft wing or wing slat, wherein the outlet plenum is located within the same interior cavity as the inlet plenum, and the outlet plenum comprises an outlet baffle capable of directing hot gases from the interior cavity through an outlet end away from the wing or wing slat.