公开(公告)号：US12221925B1

公开(公告)日：2025-02-11

申请号：US18635986

申请日：2024-04-15

Applicant: Raytheon Company

Inventor： Timothy O'Brien

IPC: F02C7/04 ,  B64D33/02 ,  F02C7/045 ,  F02C7/057 ,  F02C7/24 ,  F02K1/82 ,  F02K7/10 ,  F02K7/14 ,  F02K7/18

Abstract: A passive bypass for an inlet to a supersonic or hypersonic air-breathing engine allows airflow in the inlet to exit through the cowling when the inlet supplies more airflow than the air-breathing engine demands. The air-breathing engine may be the only form of propulsion or a secondary form of propulsion to reach higher speeds. The passive bypass includes a plurality of lower channels in the cowling that are operatively coupled to the inlet diffuser at an inner surface of the cowling and swept forward towards the throat, a plenum in the cowling operatively coupled to the plurality of lower openings and a plurality of upper channels in the cowling that are operatively coupled to the plenum and swept back away from the throat to an outer surface of the cowling. A serpentine path through the plurality of lower openings, the plenum and the plurality of upper openings allows airflow in the inlet to exit through the cowling when the inlet supplies more airflow than the air-breathing engine demands.