US 12,459,661 B2
Heat shield for an aircraft and method of using the same
Eric G. Winter, Freeland, WA (US); Leanne L. Lehman, Aliso Viejo, CA (US); William C. Cromer, Seattle, WA (US); Mark D. Gilcreest, Lynnwood, WA (US); Ryan J. Clabots, Mukilteo, WA (US); and Matthew J. Woerly, Renton, WA (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Arlington, VA (US)
Filed on Jan. 31, 2023, as Appl. No. 18/162,428.
Prior Publication US 2024/0253805 A1, Aug. 1, 2024
Int. Cl. B64D 33/08 (2006.01); B64D 27/18 (2006.01)
CPC B64D 33/08 (2013.01) [B64D 27/18 (2013.01)] 20 Claims
OG exemplary drawing
 
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.