PART INCLUDING A FIRE BARRIER

Abstract

The invention relates to a part (11) for an aircraft turbomachine, the part (11) comprising: - a body (12) comprising a composite material comprising an organic matrix and fibers embedded in the matrix, and - a fire barrier (13) arranged on at least one surface of the body (12), characterized in that the fire barrier (13) is multilayer and comprises: - a first perforated layer (14) comprising glass fibers, and - a second layer (15) comprising fibers other than the glass fibers, the first layer (14) being located between the body (12) and the second layer (15). Abstract figure: figure 2