Patent ID: 7524167

Claim:
A turbine engine sealing system comprising: a liner having an outer peripheral surface and an inner peripheral surface, the liner further having an exit end, wherein a plurality of passages extend about the liner proximate the exit end, each passage extending through the liner generally from the outer peripheral surface to the inner peripheral surface; a spring clip seal having an inner peripheral surface and an outer peripheral surface, the spring clip seal tapering from a first end having a first diameter to a second end having a second diameter that is smaller than the first diameter; and a spacer disposed between and operatively engaging each of the second end of the spring clip seal and the outer peripheral surface of the liner, the spacer being attached to outer peripheral surface of the liner, whereby the second end of the spring clip seal is spaced from the outer peripheral surface of the liner; wherein the spacer includes a plurality of notches, the spacer being positioned so that each notch is open in the direction opposite the exit of the liner and each notch is closed in the direction of the exit end of the liner effected at least partially by the continuous circumferential contact between a downstream end portion of the spacer and the outer peripheral surface of the liner in a region proximate the exit end thereof, each notch further opends to the outer peripheral surface of the liner, wherein each notch is in fluid communication with a respective one of the passages, whereby air from the combustor flow path can enter the passages.