Patent ID: 9739204
Date: 2017-08-22
CPC Classifications: F02C,F05D,Y10T

Claim:
1. A gas turbine igniter, comprising: an igniter rod configured for travel between a hot-end region and a cold-end region within a guide tube, a cap connected to the guide tube, the cap defining an access passageway for the igniter rod, a bushing attachable to an end portion of the cap that is proximate to the cold-end region, the bushing having an inner surface and an outer surface, wherein an outer surface of the bushing is threaded to engage with a threaded inner surface of the cap in said end portion of the cap, wherein a bearing is attached to the inner surface of the bushing, and wherein the inner surface of the bearing defines a guided path for the igniter rod within the cap proximate to the cold-end region.