| 主权项 |
1. A vane assembly for a gas turbine engine, comprising:
at least one vane, the or each at least one vane having a first end and an opposite second end; a first platform; and a second platform, wherein: the first end of the or each at least one vane is secured in a corresponding first aperture in the first platform; the second end of the or each at least one vane is secured in a corresponding second aperture in the second platform; the or each at least one vane intersects the first platform at an acute angle, and the or each at least one vane intersects the second platform at an obtuse angle, the acute angle and the obtuse angle being substantially supplementary; an end portion of each of the first and second ends of the or each at least one vane is tapered outwardly towards the respective first and second ends, thereby defining a first included taper angle; and a maximum width of each of the first and second ends of the or each at least one vane is less than a minimum width of the corresponding first and second apertures in respective first and second platforms. |
