Patent ID: 9500367
Filing Date: 2016-11-22
CPC Classification: F02C,F23R

Claim Text:
1. A pilot manifold system for a combustor of a gas turbine engine, comprising: a casing extending along and surrounding a combustion chamber, the casing comprising a first internal casing manifold connected to a second internal casing manifold by a pass-through hole configured to send air from the first to the second internal manifold; an air inlet in communication with the first internal casing manifold and configured to receive air from outside the casing; an end cover connected to an end of the casing, wherein the end cover contains an end cover passage configured to receive the air from the second internal casing manifold; a fuel nozzle mounted about the end cover, wherein the fuel nozzle has a pilot system that receives the air from an outlet of the end cover passage.