Snecma

Safran Aircraft Engines

Julien Szydlowski

Jonathan Langridge

Matthieu Leyko

Jean Bertucchi

Guillaume Bodard

Gabriela Philippart

Imane Ghazlane

In a cowl for a nozzle, an internal wall has a cross-section with a determined abscissa on the axis defining a neck line on the internal wall. The cowl has, downstream of the determined abscissa, indentations in the trailing edge which delimit chevrons distributed in the circumferential direction. The internal wall of the cowl diverges radially towards the interior, in a second axial half-plane passing through the tip of a chevron, from the upstream tangent on the point of the neck line in the second axial half-plane, and the lines defining the internal wall of the cowl in any axial half-plane do not have a turning point downstream of the determined abscissa of the neck line.

Nozzle of a turbomachine provided with chevrons with a non-axisymmetric inner face

A nozzle of a turbomachine is provided with chevrons with a non-axisymmetric inner face. A cover for the nozzle of longitudinal axis L-L includes an internal wall having a section with a predetermined abscissa on the L-L axis defining, on the wall, a neck line. The cover has, downstream from the abscissa, indentations in the trailing edge of the cover delimiting chevrons distributed in the circumferential direction, in which, on the cover, from the abscissa the internal wall moves away radially towards the outside of the upstream tangent, to the top of an indentation, the outer wall of the cover moves towards the upstream tangent to the top of an indentation, and the internal wall moves away radially towards the inside of the upstream tangent, to the tip of a chevron.

A heat exchanger for an air circulation channel of a turbomachine, with the heat exchanger being configured to be passed through by a fluid to be cooled, is provided. The heat exchanger includes a plurality of fins protruding with respect to a support surface, each fin extends axially over a length in the direction of the circulation of air and includes a leading edge and a trailing edge. Each fin further includes a central body, between the leading edge and the trailing edge, with the central body having, in a plane parallel to the support surface, a curved central profile.

Heat exchanger of a turbomachine

A turbomachine including a nozzle extending along an axial direction and configured to convey a hot gas stream; and a mounting pylon for mounting the turbomachme, in which the pylon extends radially from a base arranged in the vicinity of the nozzle, is provided. The turbomachine includes a pylon cooler device having at least one auxiliary gas duct having a gas inlet configured to take cold gas from the outside of the nozzle, and a gas outlet opening out in the vicinity of the base of the pylon.

Turbomachine comprising a device for the cooling of a pylon

According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.

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Montrouge, France

Julien Szydlowski