Aerodynamic link in part of a turbine engine
AssigneeSafran Aircraft Engines
InventorsThierry Kohn, Damien Cesar, Julien Sayn-Urpar
Life of this patent
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Abstract
The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings and means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.
Claims8
Part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device comprising:
- fairings extending between the two arms;
- compressible interface means interposed between the fairings;
- and
- means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.
A method for modifying an area between two arms in a stream of a turbine engine, in order to increase the aerodynamic performance of the stream, wherein each arm has an outer surface, wherein the method comprises stages in which:
- an aerodynamic linking device is used comprising fairings, compressible interface means and means for retaining the fairings in place by pressure in relation to the arms,
- the fairings are arranged so as to extend between the two arms, around a part of said outer surfaces, by interposing the compressible interface means between the fairings, and
- by the means for retaining, tension is applied to the fairings that retains the latter in place by pressure in relation to the arms, by compressing the interface means.
Dependencies are inferred from the claim text.