Arrangement for bleeding the boundary layer from an aircraft...

Details Arrangement for bleeding the boundary layer from an aircraft... Arrangement for bleeding the boundary layer from an aircraft...

2007-04-10

2007-04-10

Rodriguez, William H. (Department: 3746)

Power plants

Combustion products used as motive fluid

For nominal other than power plant output feature

C060S226100, C060S262000

Reexamination Certificate

active

10951912

ABSTRACT:
An aircraft engine comprising a nacelle, a first wall and fan outlet guide vanes. The fan outlet guide vanes comprises a plurality of stator vanes extending between a second wall and a third wall. The nacelle having apertures at a region of low pressure. A means to bleed fluid from a region of high pressure at one or more of the first wall, the second wall, the third wall or the stator vanes and at least one duct to connect the means to bleed fluid from the region of high pressure to the at least one aperture in the nacelle. The static pressure at the high pressure region is greater than that in the low pressure region such that at least some of the boundary layer of the fluid flows through the at least one duct to the at least one aperture in the nacelle.

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