NOZZLE FOR A THERMAL ANTI-ICING SYSTEM

An assembly (48) is provided for an aircraft propulsion system (20). The assembly (48) includes a nacelle inlet structure (32) with an internal cavity (82). The assembly (48) also includes a nozzle (88) configured to direct fluid into the internal cavity (82) through a plurality of ports (100) that include one or more first ports (100A) and at least one second port (100B). The nozzle (88) includes a trunk conduit (94), a first branch conduit (96) and a second branch conduit (98). The first branch conduit (96) and the second branch conduit (98) are fluidly coupled in parallel to the trunk conduit (94). The first branch conduit (96) includes the first port(s) (100A). The second branch conduit (98) includes the second port (100B).