Method for observing combustion conditions in a gas turbine engine
AssigneeRosemount Aerospace Inc.
InventorDouglas C. Myhre
Life of this patent
Estimating the term…
Abstract
A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with the fuel nozzle for observing combustor flame characteristics. The optical sensor array includes a plurality of sapphire rods positioned to be close enough to the combustor flame to oxidize soot deposits thereon.
Claims4
A method of removing soot from an optical surface of an optical sensor located within a gas turbine combustor, comprising the steps of:
- a) providing an optical sensor formed from a material that can withstand exposure to a combustor flame;
- and
- b) positioning the optical surface of the optical sensor within an air stream emanating from a fuel nozzle, in close proximity to the combustor flame so as to gain flame exposure sufficient to oxidize soot deposits thereon.
Dependencies are inferred from the claim text.