| 摘要 |
A vane assembly for a gas turbine engine comprises a plurality of vanes, with at least some of the vanes 18 configured such that when the conditions encountered by the vanes are changed, the profile / shape of the vane will alter. The vane is a composite, made of layers 20, 22 of a composite material arranged in an asymmetrical pattern relative to the mid-plane (ie., the plane extending from the leading edge to the trailing edge and through the middle of the blade). The asymmetrical layering arrangement endows asymmetrical mechanical characteristics to the blade 18. It also has associated therewith a means (eg. pistons, shape memory alloys activated by heating, opposing rings with different thermal coefficients, etc) to apply radial tension or radial compression to the vane which causes the profile of the vane to alter (see arrows 24). The composite vane may comprise an organic / metal / ceramic matrix composite, laminates of different materials, metallic material, or prestressed metal. The vane is preferably a stator guide vane. |
