Propulsion assembly for an aircraft

A propulsion assembly for an aircraft, comprising:

• a propulsion system having a core enclosed in a casing, a combustion chamber, and a turbine provided with blades that rotate about a longitudinal axis,
• a nacelle in which the propulsion system is housed, comprising cowls including a front cowl extending to a front of the turbine, with a window passing through the front cowl that is disposed at a front of the turbine, and a rear cowl extending to a rear of the turbine,
• a fire barrier that extends between the front cowl and the rear cowl,
• a supply pipe configured to convey dihydrogen, meandering inside the rear cowl as far as the rear of the turbine, then in a sealed manner through the fire barrier so as to reach the outside of the front cowl, then through said window as far as the combustion chamber, wherein the supply pipe comprises a plurality of sections that are fastened to one another and wherein an intermediate section extends from downstream of the fire barrier to downstream of the window, and
• a plate fastened in a sealed manner to the intermediate section and fastened to the front cowl so as to seal said window.