Snecma

Agnes Claire Marie Pesteil

Vincent Paul Gabriel Perrot

Fatma Ceyhun Sahin

A compressor rectifier of a turbomachine including a plurality of stationary blades extending in a circular fashion between an inner shroud and an outer shroud that are concentric and define interblade channels forming an air duct in which air to be compressed flows, the inner shroud including at least one vortex generator extending into the air duct to reduce corner vortices. The vortex generator is positioned axially in the interblade channel, between the axial position of a leading edge of the blades and those of a trailing edge thereof.

Vortex generators placed in the interblade channel of a compressor rectifier

A turbomachine including at least one bladed disk and vortex generators positioned upstream of the blading of the disk is provided. The vortex generators are of variable pitch.

Turbomachine with variable-pitch vortex generator

A method for designing a multi stage compressor of a turbomachine includes: determining the appropriate number of blades of each rotor blading; determining by instationary computations the trajectories of the slipstreams of the trailing edges of the blades of a rotor blading of an upstream stage n to the leading edges of the blades of a rotor blading of a downstream stage n+1; positioning angularly this rotor blading of the downstream stage n+1 so that the slipstreams pass substantially in the middle of the inter blade circumferential spaces of this blading; repeating these operations for all the stages in order to achieve an aerodynamic coupling on all of the rotor bladings of the compressor; and validating the respective positions of the rotor bladings by new instationary computations on the whole of the compressor.

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Alfortville, France

Agnes Claire Marie Pesteil