초록 ▼

Boundary layer air on the skin structure of an aircraft is sucked off through suction holes in the aircraft skin structure by a least one ejector pump. The ejector pump is operated by at least one of several air flow sources. One source is the excess pressure in the passenger cabin at higher altitud

Boundary layer air on the skin structure of an aircraft is sucked off through suction holes in the aircraft skin structure by a least one ejector pump. The ejector pump is operated by at least one of several air flow sources. One source is the excess pressure in the passenger cabin at higher altitudes. The other air flow source is tap air from at least one aircraft engine. If necessary, one or the other or both air supply sources may be utilized to operate the ejector pump or pumps.

대표청구항 ▼

[ What is claimed is:] [1.] An aircraft comprising an aircraft cabin, a skin structure enclosing said aircraft cabin, a suction system for sucking off boundary layer air through suction holes in said skin structure, said suction system comprising at least one ejector pump (3) including an outlet por

[ What is claimed is:] [1.] An aircraft comprising an aircraft cabin, a skin structure enclosing said aircraft cabin, a suction system for sucking off boundary layer air through suction holes in said skin structure, said suction system comprising at least one ejector pump (3) including an outlet port for ejected air, a suction port (15), and first and second flow inlet ports (13, 14), said system further comprising a suction duct (15A) connecting said suction port (15) to at least one respective suction hole (10A) of said suction holes, wherein said aircraft cabin is pressurizable for providing a source (9) of pressurized air, a pressure air duct (13A) connecting said first flow port (13) to said source (9) of pressurized air, a tap air duct (14A, 12A, 12B) connecting said second flow port (14) to an aircraft engine, and a flow control valve (5) in said tap air duct for controlling the flow of tap air from said aircraft engine to said second flow port, whereby said ejector pump (3) is operable by a flow of pressurized used cabin air when said aircraft cabin is pressurized and/or by tap air when said aircraft engine is running.