CPC B29C 69/02 (2013.01) [B29C 70/205 (2013.01); B29C 70/462 (2013.01); F02K 1/48 (2013.01); B29C 70/382 (2013.01); B29K 2101/10 (2013.01); B29L 2031/7504 (2013.01); F05D 2300/604 (2013.01)] | 11 Claims |
1. A method for manufacturing a composite material structure for a lobed structure of a gas turbine flow mixer, said flow flowing from upstream to downstream, the lobed structure having a final geometry and comprising a multilobed skirt portion having a plurality of lobes distributed around a longitudinal axis of the lobed structure, the method comprising:
a) producing, by carrying it out on a first mold, a fibrous preform comprising one of a thermoformable resin and a thermosetting resin, in a configuration having a first geometry essentially developable by post-forming to the final geometry the composite material structure to be produced, and
b) transferring on a second mold the fibrous preform having the first geometry, and, at least by exploiting the thermoformable or thermosetting nature of the resin, post-forming the first geometry, on said second mold, by deforming it to the final geometry,
wherein the first mold has an annular upstream portion and a downstream portion which flares out from the upstream cylindrical base with no lobes to form the first geometry, the annular upstream portion having a circular section and/or a cylindrical shape, and,
wherein the second mold has an annular upstream portion corresponding to the annular upstream portion of the first mold and a downstream multilobed skirt portion corresponding to the final geometry.
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