Systems and methods for cooling an inner wall of a thrust reverser of an engine of an aircraft
An engine of an aircraft includes a thrust reverser having an inner wall, which is formed by a panel assembly including an isogrid panel. An inner heat shield is coupled to a first side of the isogrid panel. An air plenum is disposed between the isogrid panel and the inner heat shield. An outer skin is coupled to a second side of the isogrid panel. The second side is opposite from the first side. One or more air inlet vent holes are formed through the isogrid panel and the outer skin. The one or more air inlet vent holes fluidly couple to the air plenum. One or more air outlet vent holes are formed through the isogrid panel and the outer skin. The one or more air outlet vent holes fluidly couple to the air plenum.
1 . A panel assembly forming an inner wall of a thrust reverser of an engine of an aircraft, wherein the thrust reverser is disposed within an aft section of a nacelle, wherein the thrust reverser comprises a first portion spaced apart from a second portion, wherein the first portion mirrors the second portion, wherein a passage extends between the first portion and the second portion, and wherein at least a portion of an engine core extends into the passage, the panel assembly comprising:
an isogrid panel which comprises a base plate, and ribs extending from the base plate, wherein recesses are formed between the base plate and the ribs;
an inner heat shield coupled to a first side of the isogrid panel, wherein an air plenum is disposed between the base plate of the isogrid panel and the inner heat shield;
an outer skin coupled to a second side of the isogrid panel, wherein the second side is opposite from the first side;
one or more air inlet vent holes formed through the isogrid panel and the outer skin, wherein the one or more air inlet vent holes fluidly couple to the air plenum; and
one or more air outlet vent holes formed through the isogrid panel and the outer skin, wherein the one or more air outlet vent holes fluidly couple to the air plenum.
2 . The panel assembly of claim 1 , wherein the outer skin faces a fan duct, and wherein the inner heat shield faces an engine core compartment.
3 . The panel assembly of claim 1 , wherein the recesses are triangular.
4 . The panel assembly of claim 1 , wherein the isogrid panel is formed from aluminum.
5 . The panel assembly of claim 1 , wherein the outer skin comprises a plurality of perforations.
6 . The panel assembly of claim 1 , further comprising a plurality of standoff bars that space the isogrid panel from the inner heat shield.
7 . The panel assembly of claim 6 , wherein the standoff bars are formed of a low conductivity material, wherein the standoff bars are longitudinally continuous between the inner heat shield and a base plate of the isogrid panel.
8 . The panel assembly of claim 1 , wherein the one or more air inlet vent holes and the one or more air outlet vent holes do not extend into the inner heat shield.
9 . The panel assembly of claim 1 , wherein the one or more air inlet vent holes are disposed at an inlet end of the panel assembly, and wherein the one or more air outlet vent holes are disposed at an outlet end of the panel assembly.
10 . The panel assembly of claim 1 , wherein the panel assembly comprises:
a lower flange;
an outwardly bowed barrel segment, wherein the lower flange is connected to the outwardly bowed barrel segment; and
an upper flange, wherein the outwardly bowed barrel segment is connected to the upper flange.
11 . A method for forming a panel assembly which forms an inner wall of a thrust reverser of an engine of an aircraft, wherein the thrust reverser is disposed within an aft section of a nacelle, wherein the thrust reverser comprises a first portion spaced apart from a second portion, wherein the first portion mirrors the second portion, wherein a passage extends between the first portion and the second portion, and wherein at least a portion of an engine core extends into the passage, the method comprising:
coupling an inner heat shield to a first side of an isogrid panel which comprises a base plate, and ribs extending from the base plate, wherein recesses are formed between the base plate and the ribs, wherein an air plenum is disposed between the base plate of the isogrid panel and the inner heat shield;
coupling an outer skin coupled to a second side of the isogrid panel, wherein the second side is opposite from the first side;
forming one or more air inlet vent holes through the isogrid panel and the outer skin;
forming one or more air outlet vent holes formed through the isogrid panel and the outer skin, wherein the one or more air outlet vent holes fluidly couple to the air plenum; and
forming, with the panel assembly, the inner wall of the thrust reverser of the engine of the aircraft.
12 . The method of claim 11 , wherein the outer skin faces a fan duct, and wherein the inner heat shield faces an engine core compartment.
13 . The method of claim 11 , wherein the recesses are triangular.
14 . The method of claim 11 , wherein the isogrid panel is formed from aluminum.
15 . The method of claim 11 , wherein the outer skin comprises a plurality of perforations.
16 . The method of claim 11 , further comprising spacing, by a plurality of standoff bars, the isogrid panel from the inner heat shield.
17 . The method of claim 11 , wherein the one or more air inlet vent holes and the one or more air outlet vent holes do not extend into the inner heat shield.
18 . The method of claim 11 , wherein the one or more air inlet vent holes are disposed at an inlet end of the panel assembly, and wherein the one or more air outlet vent holes are disposed at an outlet end of the panel assembly.
19 . An engine for an aircraft, the engine comprising:
a thrust reverser having an inner wall, wherein the inner wall is formed by a panel assembly, wherein the thrust reverser is disposed within an aft section of a nacelle, wherein the thrust reverser comprises a first portion spaced apart from a second portion, wherein the first portion mirrors the second portion, wherein a passage extends between the first portion and the second portion, and wherein at least a portion of an engine core extends into the passage,
the panel assembly comprising:
an isogrid panel comprising a base plate, and ribs extending from the base plate, wherein triangular recesses are formed between the base plate and the ribs;
an inner heat shield coupled to a first side of the isogrid panel, wherein an air plenum is disposed between the base plate of the isogrid panel and the inner heat shield, and wherein the inner heat shield faces an engine core compartment;
a plurality of standoff bars that space the isogrid panel from the inner heat shield;
an outer skin coupled to a second side of the isogrid panel, wherein the second side is opposite from the first side, wherein the outer skin comprises a plurality of perforations, and wherein the outer skin faces a fan duct;
one or more air inlet vent holes formed through the isogrid panel and the outer skin, wherein the one or more air inlet vent holes fluidly couple to the air plenum; and
one or more air outlet vent holes formed through the isogrid panel and the outer skin, wherein the one or more air outlet vent holes fluidly couple to the air plenum.
20 . The engine of claim 19 , wherein the each of the one or more air inlet vent holes and the one or more air outlet vent holes are formed by a metal tube, wherein the one or more air inlet vent holes and the one or more air outlet vent holes do not extend into the inner heat shield, wherein the one or more air inlet vent holes are disposed at an inlet end of the panel assembly, and wherein the one or more air outlet vent holes are disposed at an outlet end of the panel assembly.