초록 ▼

An improvement to supersonic laminar flow control suction systems, including an inlet air duct (32) for providing subsonic ram engine inlet air, is provided. The inlet air duct (32) supplies air pressure power to one or more turbines of suction system compressor units alone for flight conditions at

An improvement to supersonic laminar flow control suction systems, including an inlet air duct (32) for providing subsonic ram engine inlet air, is provided. The inlet air duct (32) supplies air pressure power to one or more turbines of suction system compressor units alone for flight conditions at or above a particular minimum speed and minimum altitude, and in conjunction with engine compressor bleed air for flight conditions below the minimum speed and minimum altitude. The inlet air duct (32) is angled in the direction of subsonic airflow approximately 30 degrees from the horizontal off an opening in an upper wall of a subsonic diffuser of an engine inlet on a supersonic aircraft, and is connected to a power input line that feeds one or more compressor unit turbines. A check valve prevents backflow of air toward the engine inlet. The suction system further includes a short compressor output duct (38) and a short turbine output duct (40). These two ducts join to form a single exhaust passage (42), ensuring a moderate overall suction air exhaust gas temperature.

대표청구항 ▼

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] In a boundary layer flow control suction system for an aircraft including a supersonic engine inlet having a region of subsonic airflow, a source of engine bleed air, and a boundar

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] In a boundary layer flow control suction system for an aircraft including a supersonic engine inlet having a region of subsonic airflow, a source of engine bleed air, and a boundary layer suction compressor unit having a turbine driving a compressor, the compressor being connected to a suction surface of the aircraft for suctioning external air from an aircraft surface;the improvement comprising a turbine input line connected to both the region of subsonic airflow and the source of engine bleed air during flight at less than a predetermined minimum aircraft speed M.sub.min and minimum aircraft altitude A.sub.min, and connected only to the region of subsonic airflow during flight at at least the M.sub.min and A.sub.min ;whereby the turbine is powered from air flowing through the turbine input line during boundary layer flow control.