| US 7,524,167 B2 | ||
| Combustor spring clip seal system | ||
| Rajeev Ohri, Winter Springs, Fla. (US); and Plum Boonsuan, Greenville, S.C. (US) | ||
| Assigned to Siemens Energy, Inc., Orlando, Fla. (US) | ||
| Filed on May 04, 2006, as Appl. No. 11/418,065. | ||
| Prior Publication US 2007/0258808 A1, Nov. 08, 2007 | ||
| Int. Cl. F01D 25/24 (2006.01) | ||
| U.S. Cl. 415—215.1 [277/544; 277/545; 277/546; 60/752; 60/800] | 17 Claims |

| 1. 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.
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