Patent ID: 8104772

Claim:
A seal for containment of gases during ultra high temperature operations between gas turbine nozzles downstream of a combustion chamber, separating a high pressure area on one side from a low pressure area on an opposite side, said seal formed to convert axial displacements into radial movements thereby eliminating axial strains, including two engaging, conical ring structures, each comprising: cross-sections with a tapering arcuate side facing radially away from said high pressure area; an axial distal end having a larger diameter than an opposite end for engaging a flat annular surface on an adjacent structural member; each of said conical ring structures has a side opposite said tapering arcuate side that is cylindrical with a cylindrical diameter that is concentric with said arcuate side; and at least one heat-destructible, approximately cylindrical wax spacer concentric with said conical ring structure, and positioned adjacent said conical ring structure, opposite said tapering arcuate side, to aid in correct positioning during assembly for subsequent high temperature operation.