Exhaust nozzle assembly for aircraft propulsion system

An apparatus for an aircraft propulsion system, comprising:

• an exhaust nozzle comprising a nozzle wall and a nozzle ring, the nozzle wall extending axially along an axis from an upstream end of the nozzle wall to a downstream end of the nozzle wall, the nozzle wall extending circumferentially around the axis, an inner side of the nozzle wall forming an outer peripheral boundary of a propulsion system flowpath axially along the nozzle wall, the nozzle ring forming a downstream trailing edge of the exhaust nozzle, the nozzle ring projecting axially out from the downstream end of the nozzle wall to the downstream trailing edge of the exhaust nozzle to form another outer peripheral boundary of the propulsion system flowpath axially along the nozzle ring, the nozzle ring comprising a plurality of blind apertures arranged circumferentially about the axis, and each of the plurality of blind apertures projecting radially inward towards the axis partially into the nozzle ring;
• a fire seal disposed radially outboard of the nozzle ring, the fire seal axially and circumferentially overlapping the nozzle ring;
• and
• a plurality of fasteners mounting the fire seal to the nozzle ring, each of the plurality of fasteners including a shank and a head, the shank projecting longitudinally out from the head, through the fire seal, and threaded into a respective one of the blind apertures, and the fire seal radially clamped between the head of each of the plurality of fasteners and the nozzle ring.

An apparatus for an aircraft propulsion system, comprising:

• an exhaust nozzle comprising a chevron ring, the chevron ring extending axially along an axis to and forming a downstream trailing edge of the exhaust nozzle, the chevron ring including a ring base and a plurality of chevrons arranged circumferentially about the axis along the downstream trailing edge of the exhaust nozzle, the ring base comprising a plurality of blind apertures arranged circumferentially about the axis, and each of the plurality of blind apertures projecting radially inward towards the axis partially into the ring base;
• a fire seal disposed radially outboard of the chevron ring, the fire seal axially and circumferentially overlapping the ring base;
• and
• a plurality of fasteners mounting the fire seal to the chevron ring, each of the plurality of fasteners including a shank and a head, the shank projecting longitudinally out from the head, through the fire seal, and threaded into a respective one of the blind apertures, and the fire seal radially clamped between the head of each of the plurality of fasteners and the ring base;
• wherein the exhaust nozzle further comprises
• a fairing skin disposed radially between the fire seal and the ring base;
• the shank projecting longitudinally through the fairing skin;
• and
• the fire seal and the fairing skin radially clamped between the head of each of the plurality of fasteners and the ring base.