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AssigneeSafran Aircraft Engines
InventorsThomas Nolwenn Emmanuel Delahaye, Kamel Benderradji, Alain Marc Lucien Bromann, Liliana Gomes Pereira, Delphine Hermance Maxime Parent
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An angular sector of a fixed blade ring of a turbomachine, in particular a stator or a guide vane assembly, includes, relative to the axis of said fixed blade ring, a radially outer platform, a radially inner platform, at least two blades extending between said platforms, and at least one block of abradable honeycomb material extending on the inside of the inner platform between transverse ends of the sector. The block of abradable material includes at least one transverse end wall shaped according to a toothed profile having at least one radially oriented tooth extending across an entire radial thickness of said block.
A fixed blading ring of a turbomachine made of multiple angular sectors, each angular sector extending at a given angle around an axis A of the fixed blading ring and comprising, relative to the axis A, a radially outer platform, a radially inner platform, at least two vanes extending between said radially outer and radially inner platforms, and one honeycomb structure extending between transverse ends of each sector, said honeycomb structure comprising at least one abradable honeycomb material block extending on an inside of the radially inner platform between the transverse ends of said angular sector, wherein the abradable honeycomb material block comprises at least one transverse end wall shaped according to a toothed profile comprising at least one tooth with a radial direction, said at least one tooth extending along an entire radial thickness of said abradable honeycomb material block.
Dependencies are inferred from the claim text.