Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Marcel J Tournere

Pierre Debeneix

Jacques L Drouet

A multiflow turbojet engine secondary flow adjusting device which includes annular vanes regularly distributed around the secondary duct. The vanes are movable about two fixed axes disposed between one half and one third of the height of the duct when the vane is in the active position. A control mechanism for the vanes are disposed within the interior of the duct and act on the axis of radial symmetry and at two-thirds of the height of the duct when the vane is in the active position. In the inactive position, the vane is parallel to the secondary air flow. The actuator and the fixed support axes form a modular assembly in accordance with another embodiment.

Multiflow turbo jet engine secondary flow adjusting device

The invention concerns an impact cooling device for the packing rings of turbine of a turbojet engine. The flow of cooling air entering an enclosure concentric to the rings, is divided into two distinct ventilation circuits by means of a ferrule of a generally circular shape, having corrugations, and with the amplitudes of said corrugations decreasing from upstream to downstream.

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Paris, France

Marcel J Tournere