▎ 摘　　要

NOVELTY - The lip (40) has an upstream annular wall (46) connecting an external annular wall (42) and an internal annular wall (44) to delimit an annular cavity (400). A part of the lip comprises a thermal transfer coating (6), which comprises an allotropic carbon material i.e. graphene. The coating is located on portions of a surface of the lip. An acoustic annular panel is located in the cavity, and extends around of the internal annular walls. Each internal annular wall is perforated, and comprises holes opening into acoustic cells of the panel. The panel is made of metal alloy, composite or thermoplastic. USE - Annular air inlet lip for a nacelle of an aircraft propulsion assembly (claimed) e.g. turbomachine such as turbofan engine, of an aircraft. ADVANTAGE - The allotropic carbon coating can improve conductive and radiative heat transfer from the cavity of the lip to the walls of the lip and from the cavity to the walls of an acoustic annular panel when placed on the inner wall to heat the lip area under the acoustic panel by radiation. DETAILED DESCRIPTION - An INDEPENDENT CLAIM is also included for a method for manufacturing an annular air inlet lip. DESCRIPTION OF DRAWING(S) - The drawing shows a perspective view of an air inlet lip. 6Thermal transfer coating 40Annular air inlet lip 42External annular wall 44Internal annular wall 46Upstream annular wall 400Annular cavity