公开(公告)号：US12037940B2

公开(公告)日：2024-07-16

申请号：US18247037

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Hazem Kioua ,  Emmanuel Lesteven

IPC: F02C7/04 ,  F02C7/047

CPC classification number: F02C7/047 ,  F05D2220/80

Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: •⋅ pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •⋅ a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •⋅ at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •⋅ at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.

公开(公告)号：US20240018902A1

公开(公告)日：2024-01-18

申请号：US18247037

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Hazem Kioua ,  Emmanuel Lesteven

IPC: F02C7/047

CPC classification number: F02C7/047 ,  F05D2220/80

Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: a pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, a speed reducer fixedly mounted inside the pipe along the longitudinal axis, at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.