Aircraft sidewall having cabin windows with insulating seals
A window assembly for an aircraft fuselage includes a seal surrounding the periphery of a window in a cabin sidewall. The seal fills voids within the sidewall and forms a physical and thermal barrier against cold air within the sidewall cavity from reaching the window.
1 . A window assembly for aircraft having an outer skin and an inner sidewall panel separated by a sidewall cavity, comprising:
a window frame configured to be attached to the outer skin;
a window mounted on the window frame; and
a seal surrounding the window inside the sidewall cavity, the seal being configured to form a barrier preventing cold air inside the cavity from reaching the window, and wherein the seal is formed of a type of insulating thermal material, and wherein the seal includes a flange in face-to-face contact with the inner sidewall panel and completely surrounding the window.
2 . The window assembly of claim 1 , wherein the seal is rigid foam.
3 . The window assembly of claim 2 , wherein the rigid foam is polyvinylidene fluoride.
4 . The window assembly of claim 1 , wherein the seal is of one-piece unitary construction.
5 . The window assembly of claim 1 , wherein the seal includes a rib completely surrounding the window and connected with the flange.
6 . The window assembly of claim 5 , wherein the flange and the rib are integrally formed together.
7 . The window assembly of claim 1 , further comprising a layer of insulation interposed between the seal and the inner sidewall panel.
8 . The window assembly of claim 1 , wherein:
the sidewall cavity includes voids adjacent the window, and
the seal fills the voids.
9 . An aircraft fuselage, comprising:
an outer skin;
an inner sidewall panel separated from the outer skin by a sidewall cavity;
insulation within the sidewall cavity configured to thermally insulate the inner sidewall panel from the outer skin;
at least one window frame attached to the outer skin;
a window mounted on the window frame; and
a seal surrounding the window and configured to insulate the window from the sidewall cavity, and wherein the seal is formed of a type of insulating thermal material, and wherein the seal includes a flange pressed against and in face-to-face contact with the inner sidewall panel.
10 . The aircraft fuselage of claim 9 , further comprising an airframe having sculptured sections in which the sidewall cavity has reduced thickness.
11 . The aircraft fuselage of claim 9 , wherein the seal is closed cell foam.
12 . The aircraft fuselage of claim 9 , wherein the seal includes:
a rib extending outwardly from the flange.
13 . The aircraft fuselage claim 12 , wherein the flange and the rib are integrally formed as a single piece.
14 . The aircraft fuselage of claim 9 , wherein the seal forms a physical barrier between the window and the sidewall cavity preventing a convection airflow within the sidewall cavity from reaching the window.
15 . The aircraft fuselage of claim 9 , further comprising:
a layer of insulation interposed between the seal and the inner sidewall panel.
16 . The aircraft fuselage of claim 9 , further comprising a layer of insulation in face-to-face contact with the inner sidewall panel and fitted around a periphery of the window.
17 . A method of insulating an aircraft cabin window from cold air inside sidewall cavity, comprising:
installing a seal around the window in face-to-face contact with a sidewall of the cabin, wherein the seal is formed of a type of insulating thermal material, and wherein the seal includes a flange that completely surrounds the window.
18 . The method of claim 17 , wherein installing the seal includes placing the seal in voids within the sidewall cavity.
19 . The method of claim 17 , wherein installing the seal includes compressing the seal against the sidewall.
20 . The method of claim 17 , wherein installing the seal includes attaching the seal to a window assembly.