Patent ID: 7090463
Filing Date: 2006-08-15
Classification: F01D,F04D,F05D

Abstract:
1. A guide vane for a gas turbine engine, the guide vane comprising a first end, a second end, a first longitudinal edge, a second longitudinal edge and sheet portions being bonded along the first and second longitudinal edges, the sheet portions being deformed to form a cavity therebetween, the deformed sheet portions defining a non linear variation in maximum chordal thickness along the guide vane between the first end and the second end of the guide vane wherein each sheet portion being convex outwardly between the first end and the second end of the guide vane wherein the maximum chordal thickness increasing from the first end to a greater maximum chordal thickness at a central portion of the guide vane between a first end and a second end, the maximum chordal thickness decreasing from the central portion to the second end, the cavity increasing in width from the first end to a maximum width at the central portion and the cavity decreasing in width from the maximum width at the central portion to the second end.