Safran Aircraft Engines

Snecma

Pradeep Cojande

Hanna Reiss

Eva Julie Lebeault

Benjamin Bulot

Ghislain Maxime Romuald Madiot

Pierre Grégoire Anton

Eric Pierre Maurice Lippinois

Hélène Madeleine Nicole Deparis

Eric Pierre Lippinois

A discharge duct () of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end () and an outlet end (), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill () arranged at the outlet end (), the ejection grill () comprising a plurality of fins (), characterised in that the fins () comprise flow channels () for a fluid to be cooled, so as to form a heat exchange system.

Discharge duct of an intermediate housing hub for an aircraft turbojet engine comprising cooling channels

A disclosed propulsion unit includes a pylon having a blade presenting a chord Cx and a downstream arm having a structural arm. The pylon has a first distance D between a trailing edge of a fan blade and a leading edge of the fan blade, a second distance d between said trailing edge of the blade and a leading edge of the structural arm, and a third distance L between the trailing edge of the blade and a mark located at a maximum thickness of the downstream arm. The pylon is dimensioned according to: a first quotient between D and Cx between 2.2 and 2.6, a second quotient between d and Cx between 1 and 1.2, and a third quotient between L and Cx between 4 and 7.

Pylon of a propulsion unit

A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.

Turbomachine guide vanes with improved vane profile

An outlet guide vane for a turbine engine, the vane having a plurality of vane sections stacked along a radial axis Z. Over a bottom portion of the vane in the range 0 to 50% of its total height, the leading edge of each section is in front of the leading edge of the corresponding section at the total height, and the maximum thicknesses are located at positions that are offset from the leading edge by at least 50% of the chord.

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Moissy-Cramayel, France

Pradeep Cojande