Thermal anti-icing system for aircraft

• US 5,011,098 A
• Filed: 12/30/1988
• Issued: 04/30/1991
• Est. Priority Date: 12/30/1988
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Orr, William W., McLaren, Douglas
• Primary Examiner(s): Barefoot, Galen
• Application Number:
  US07/292,541
• Time in Patent Office: 851 Days
• Field of Search: 246/117 A, 246/134 R, 246/134 B, 246/133, 60/39.093
• US Class Current: 244/134.00B
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: B64D 2027/005 Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• CPC Class Codes: B64D 27/14 within, or attached to, fuselages
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Thermal anti-icing systems for aircraft and methods for fabricating such systems. The anti-icing systems have an integrated one-piece skin with passageways formed therein to supply a heated fluid to that portion of an aircraft structure where anti-icing is desired. The anti-icing system also has an integrated or separately supplied manifold for routing heating fluid to the anti-icing system flow passages. The anti-icing system can be used in the leading edges of such aircraft structures as wings, horizontal and vertical stabilizers, inboard and outboard slats, engine struts, and engine cowls. A method for fabricating of aircraft structures with integral anti-icing systems of the character just described is also disclosed.

Claims

1. The combination of an aircraft structure having a leading edge and a system for heating said structure to inhibit the formation of ice on said leading edge, said structure having an outer skin with spaced apart, exposed surface defining segments and said heating system including:

a. an inner skin with a segment of complementary configuration adjacent a segment of said outer skin and cooperating therewith to form a series of flow passages which;

are disposed in side-by-side relationship, extend from the leading edge of said structure toward the rear thereof, and have inlets at the leading edge of the structure and outlets to the rear of said inlets;

b. a bulkhead so extending spanwise of said structure between the inlets and outlets of said flow passages and from one side to the other of said structure as to form a heated fluid inlet plenum that keeps fluid from escaping toward the rear of the structure;

c. a heated fluid supply manifold;

located in said structure on the forward side of said bulkhead, spanning said series of fluid flow passages, and having outlet passages at intervals along the length of the manifold through which the heated fluid can flow into the inlet plenum;

d. means bonding said outer skin to said inner skin and said manifold to said bulkhead; and

e. means for effecting a flow of a heated fluid;

into said supply manifold, from said manifold toward the leading edge of said structure, through said inlets into said flow passages, through said passages, and from said outlets to thereby affect a transfer of thermal energy from said fluid to the outer skin of said structure to heat said skin and thereby inhibit the formation of ice on that skin.

2. A combination as defined in claim 1, wherein the outlet passages from said heated fluid supply manifold are arranged in sets and wherein, in each set, there are a first outlet passage for directing the heated fluid from said manifold toward one of the segments of the outer skin of the structure and a second outlet passage for directing said fluid from said manifold toward the other of the segments of said skin.

3. A combination as defined in claim 1, wherein said bulkhead has one integral edge portion extending along and engaging a segment of said outer skin on one side of said structure and a second integral edge portion extending along, and engaging, a segment of said inner skin on the other side of said structure, said second edge portion being configured to match that segment of the inner skin on said other side of said structure.

4. A combination as defined in claim 1 wherein the heating system includes means for collecting and dumping overboard the fluid discharged from said flow passages through said outlets, said last-mentioned means comprising:

a. a second bulkhead extending spanwise within said structure and from one to the other of the segments of the outer skin, said bulkhead having edge portions meeting the segments of said outer skin, and thereby cooperating with said outer skin to define an exhaust plenum for the heated fluid;

b. a fluid exhaust duct having an inlet portion and an outlet portion, said inlet portion communicating with said exhaust plenum and said outlet portion communicating with the ambient surroundings, whereby fluid discharged from said fluid passageways and collected in said exhaust plenum may be dumped overboard.

5. A combination as defined in claim 1, wherein the outlet passages from said heated fluid supply manifold are arranged in sets and wherein, in each set, there are:

a. a first outlet passage for directing the heated fluid from said manifold toward one of the segments of the outer skin of the structure so that the heated fluid impinges upon the internal portion of said outer skin adjacent said outlet,

b. a second outlet passage for directing said fluid from said manifold toward the same segment of said skin, so that the heated fluid impinges upon the internal portion of said outer skin adjacent said second outlet, and a third outlet passage for directing said fluid from said manifold toward the same segment of said skin, so that the heated fluid impinges upon the internal portion of said outer skin adjacent to said third outlet.

6. A combination as defined in claim 1, wherein said heating fluid supply manifold is metallurgically bonded to the upstream side of said bulkhead.

7. A combination as defined in claim 1, wherein said leading edge structure is displaceably supported from a separate aircraft component.

8. A combination as defined in claim 1, wherein said leading edge structure is a wing, an engine supporting strut, an engine cowling, or a horizontal or vertical stabilizer.

9. A combination as defined in claim 1, wherein the flow passages of the heating system extend from the leading edge of the leading edge structure toward the trailing edge thereof.

10. A combination as defined in claim 1 which also includes:

a. a heated fluid supply line in and extending spanwise of said structure; and

b. means providing fluid communication between said fluid supply line and said manifold.

11. A combination as defined in claim 10 in which said heated fluid supply line is located in said manifold.

12. A combination as defined in claim 10 in which the heated fluid supply line is located on the opposite side of said bulkhead from said manifold.