Boundary layer suction arrangement

Details Boundary layer suction arrangement Boundary layer suction arrangement

B - Operations, Transporting

64

C

B64C 21/06 (2006.01)

Patent

CA 2565011

The invention pertains to a suction arrangement for drawing off boundary layers on an aircraft with a structure, the outer skin of which contains suction surfaces in critical flow areas, and with at least one air breathing engine. Bleed air is withdrawn from the high-pressure region (P) of the engine (1) by means of a branch line (10) and used for driving the turbine (20) of a turbo-supercharger assembly (2), the compressor (24) of which serves as the suction source for drawing off the boundary layer.

L'invention concerne un système d'aspiration permettant de soutirer les couches limites d'un avion ayant une structure dont l'enveloppe externe contient des surfaces d'aspiration dans des zone d'écoulement critique, et au moins un moteur aérobie. L'air de prélèvement est tiré d'une zone haute pression (P) du moteur (1) à l'aide d'une conduite dérivée (10) et est utilisé pour commander la turbine (20) d'un ensemble turbo-superchargeur (2) dont le compresseur (24) sert de source d'aspiration pour tirer la couche limite.

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