Patent ID: 8016297
Filing Date: 2011-09-13
Classification: F01D

Abstract:
1. A gas turbine engine sealing element comprising: an annular seal body having an inner diameter and an outer diameter, the seal body extending along an axis of symmetry between a first end and a second end; the seal body being formed of a strip of material having first and second opposing edges, the strip of material being deformed to exhibit a first sealing surface at the first end, a second sealing surface at the second end, the seal body exhibits at least two corrugations, each corrugation having a ridge and a trough between the first end and the second end, and a third sealing surface along the inner diameter, the third sealing surface located radially inward from and axially between the first sealing surface and the second sealing surface so as to be biased radially inward, the first edge being located adjacent to the third sealing surface, the second edge being located adjacent to the second sealing surface; wherein the first edge is spaced from the second edge to define an annular opening, the annular opening providing access to an annular cavity of the seal body, the seal body exhibits a continuous curve between the second sealing surface and the third sealing surface and the third sealing surface comprises a straight portion of the seal body.