Patent ID: 8468831

Claim:
A premixed pilot assembly configured to be coupled to a fuel nozzle for a turbine combustor, the premixed pilot assembly including: a first cylinder, a second cylinder, configured to hold a selected one of: pilot fuel or air, the second cylinder disposed within the first cylinder such that an annular area is formed between the first cylinder and the second cylinder, the annular area configured to allow the other one of the pilot fuel or air to flow through the annular area; a tip, coupled to the second cylinder, the tip configured to create at least one second cylinder opening to direct the selected one of the pilot fuel or the air flowing through the second cylinder radially outward, perpendicular to the annular area; and an end piece, coupled to the first cylinder, the end piece configured to create at least one first cylinder opening to direct the other one of the pilot fuel or air flowing through the annular area radially inward, perpendicular to the annular area, directly towards the selected one of the pilot fuel or the air directed from the at least one second cylinder opening.