公开(公告)号：US11220958B2

公开(公告)日：2022-01-11

申请号：US16674095

申请日：2019-11-05

Applicant: Airbus Operations SAS

Inventor： Maxime Zebian

IPC: F02C7/047 ,  F01D25/02 ,  F02C6/08 ,  B64D33/02 ,  B64D15/04

Abstract: A turbomachine comprising an engine body and an annular nacelle. The nacelle has an air intake comprising an outer skin, an inner skin, an air intake lip connecting the outer and inner skins together, and an annular frame connecting the outer and inner skins together. The turbomachine comprises a system for de-icing the air intake having an air bleeding port for bleeding a flow of hot air from the engine body, and two interconnected heating systems. An inner skin heating system receives the hot air flow to heat, by means of a gas-liquid heat exchanger, a heat transfer liquid contained in a hydraulic circuit arranged in part in the heat exchanger and in the inner skin. An air intake lip heating system diffuses the flow of hot air, once it has passed through the inner skin heating system, through the annular frame to heat the air intake lip.