Heat shield for an aircraft and method of using the same

Patent metadata

Field	Value
Publication number	US-12459661-B2
Application number	US-202318162428-A
Country	US
Kind code	B2
Filing date	Jan 31, 2023
Priority date	Jan 31, 2023
Publication date	Nov 4, 2025
Grant date	Nov 4, 2025

Abstract

There is provided a heat shield for an aircraft. The heat shield has a pair of side skins. Each side skin is formed of a heat resistant material and has a side skin edge. The heat shield further has a lower skin formed of a heat resistant material and having lower skin edges. The lower skin edges extend an extended length past the side skin edges. The lower skin edges are separate from the side skin edges. A gap is formed between the side skin edges and the lower skin. The lower skin is configured to thermally expand without contacting the pair of side skins. The heat shield further has a plurality of frame members attached to the lower skin. The heat shield further has an air ingress restrictor assembly associated with one of, the pair of side skins, or the lower skin.

First claim

The invention claimed is:

1 . A heat shield for an aircraft, the heat shield comprising:
a pair of side skins, each side skin formed of a heat resistant material and having a side skin lower edge; a lower skin formed of a heat resistant material and having lower skin edges, the lower skin edges extending an extended length past the side skin lower edges, the lower skin edges being separate from the side skin lower edges, and a gap formed between the side skin lower edges and the lower skin, and the lower skin configured to thermally expand without contacting the pair of side skins, the gap having a gap width in a range of from 0.1 inch to 0.25 inch, and the gap accommodating thermal expansion of the lower skin resulting from a heated exhaust gas discharged from a jet engine positioned forward of the heat shield, and the gap preventing formation of a conduction path between the pair of side skins and the lower skin, and the extended length being in a range of from 1.0 inch to 6.0 inches, and the extended length shielding each side skin and each gap from the heated exhaust gas, the extended length blocking flow of the heated exhaust gas into an internal cavity of the heat shield, and the extended length allowing for conduction path prevention; a plurality of frame members attached to the lower skin; and an air ingress restrictor assembly comprising a first seal member and a second seal member plugging the gap between the side skin lower edges and the lower skin, each of the first seal member and the second seal member positioned adjacent to, and contacting, the side skin lower edges and lower skin portions of the lower skin, the lower skin portions positioned across from the side skin lower edges, the air ingress restrictor assembly configured to restrict air flow between the pair of side skins and the lower skin, into the heat shield, and the air ingress restrictor assembly restricting the flow of the heated exhaust gas into the internal cavity of the heat shield, wherein, the lower skin edges being separate from the side skin lower edges reduces a risk of fatigue of the heat shield.

2 . The heat shield of claim 1 , wherein the heat resistant material of the pair of side skins and the heat resistant material of the lower skin each comprises one of, a composite material, or a metal material.

3 . The heat shield of claim 2 , wherein the composite material comprises a ceramic matrix composite material.

4 . The heat shield of claim 2 , wherein the metal material comprises titanium, nickel alloy, or stainless steel.

5 . The heat shield of claim 1 , wherein the heat resistant material is configured to withstand temperatures in a temperature range of from 500 degrees Fahrenheit to 1500 degrees Fahrenheit.

6 . The heat shield of claim 1 , wherein the heat shield is a strut aft fairing heat shield.

7 . The heat shield of claim 1 , wherein the heat shield eliminates a structural joint between each side skin and the lower skin.

8 . The heat shield of claim 1 , wherein the gap preventing formation of the conduction path between the pair of side skins and the lower skin reduces heating of the pair of side skins and reduces a temperature on the side skin lower edges.

9 . The heat shield of claim 1 , wherein the first seal member and the second seal member each comprises one of, a bulb seal, a thermal barrier seal, a segmented seal, a knit ceramic seal, a blade seal, or an aero seal.

10 . The heat shield of claim 1 , wherein the first seal member and the second seal member each has a forward end, an aft end, and an elongate body formed between the forward end and the aft end.

11 . An aircraft comprising:
a fuselage; at least one wing attached to the fuselage; two or more jet engines attached to the at least one wing, each jet engine configured to exhaust a heated exhaust gas, and each jet engine having a fan configured to exhaust a cooling fan flow air stream; and a heat shield positioned adjacent to each jet engine, the heat shield comprising:
a pair of side skins, each side skin formed of a heat resistant material and having a side skin lower edge;
a lower skin formed of a heat resistant material and having lower skin edges, the lower skin edges extending an extended length past the side skin lower edges, the lower skin edges being separate from the side skin lower edges, and a gap formed between the side skin lower edges and the lower skin, and the lower skin configured to thermally expand without contacting the pair of side skins, the gap having a gap width in a range of from 0.1 inch to 0.25 inch, and the gap accommodating thermal expansion of the lower skin resulting from the heated exhaust gas, and the gap preventing formation of a conduction path between the pair of side skins and the lower skin, and the extended length being in a range of from 1.0 inch to 6.0 inches, and the extended length shielding each side skin and each gap from the heated exhaust gas, the extended length blocking flow of the heated exhaust gas into an internal cavity of the heat shield, and the extended length allowing for conduction path prevention;
a plurality of frame members attached to the lower skin; and
an air ingress restrictor assembly comprising a first seal member and a second seal member plugging the gap between the side skin lower edges and the lower skin, each of the first seal member and the second seal member positioned adjacent to, and contacting, the side skin lower edges and lower skin portions of the lower skin, the lower skin portions positioned across from the side skin lower edges, the air ingress restrictor assembly configured to restrict air flow between the pair of side skins and the lower skin, into the heat shield, and the air ingress restrictor assembly restricting the flow of the heated exhaust gas into the internal cavity of the heat shield,
wherein, the lower skin edges being separate from the side skin lower edges reduces a risk of fatigue of the heat shield.

12 . The aircraft of claim 11 , further comprising a strut aft fairing positioned adjacent to the heat shield.

13 . The aircraft of claim 11 , wherein the heat resistant material of the pair of side skins and the heat resistant material of the lower skin each comprises one of, a composite material, or a metal material.

14 . The aircraft of claim 11 , wherein the first seal member and the second seal member each comprises one of, a bulb seal, a thermal barrier seal, a segmented seal, a knit ceramic seal, a blade seal, or an aero seal.

15 . The aircraft of claim 11 , wherein the first seal member and the second seal member each has a forward end, an aft end, and an elongate body formed between the forward end and the aft end.

16 . A method of using a heat shield in an aircraft, the method comprising the steps of:
providing the heat shield positioned adjacent to a jet engine of the aircraft, the heat shield comprising:
a pair of side skins, each side skin formed of a heat resistant material and having a side skin lower edge;
a lower skin formed of a heat resistant material and having lower skin edges, the lower skin edges extending an extended length past the side skin lower edges, the lower skin edges being separate from the side skin lower edges, and a gap formed between the side skin lower edges and the lower skin, the gap having a gap width in a range of from 0.1 inch to 0.25 inch, and the gap accommodating thermal expansion of the lower skin resulting from a heated exhaust gas discharged from the jet engine, and the gap preventing formation of a conduction path between the pair of side skins and the lower sk

Assignees

• Boeing Co

Inventors

• Winter Eric G
• Lehman Leanne L
• Cromer William C
• Gilcreest Mark D
• Clabots Ryan J
• Woerly Matthew J

Classifications

• B64D27/18

  within, or attached to, wings · CPC title

• B64C1/40

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• B64D33/08 Primary

  of power plant cooling systems · CPC title

• B64C1/38 Primary

  Constructions adapted to reduce effects of aerodynamic or other external heating · CPC title