Powerplant for an aircraft

A powerplant for an aircraft comprising:

• a nacelle,
• a propulsion system housed in the nacelle and comprising a core enclosed in a casing and having a combustion chamber,
• a supply pipe configured to convey dihydrogen to the combustion chamber by passing through the casing in an injection zone,
• at least one treatment system arranged on the supply pipe and configured for treating said dihydrogen conveyed in the supply pipe, and
• a closed enclosure, delimited by a first wall and a second wall, and containing a downstream pipe of the supply pipe, at least one treatment system, and the injection zone, wherein the first wall is formed by part of the casing,
• wherein said closed enclosure is formed by a first sub-enclosure containing the injection zone, and a second sub-enclosure separated from the first sub-enclosure by a separating wall,
• wherein the downstream pipe passes through the second sub-enclosure and then the first sub-enclosure to reach the injection zone by passing through the separating wall,
• wherein each sub-enclosure is closed and delimited by a first wall, a second wall, and the separating wall, and
• wherein the first wall defining each sub-enclosure is formed by part of the casing.