Systems and methods for cooling an inner wall of a thrust reverser of an engine of an aircraft

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.

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.