Patent ID: 8528334
Filing Date: 2013-09-10
Classification: F23R

Abstract:
1. An injector for a gas turbine combustor comprising: an inner wall, at least one catalyst coated surface disposed within said inner wall and forming at least one passage adapted to provide a feed gas flow through the injector, at least one channel disposed within said inner wall and adapted for passage of an oxidant gas flow through the injector, at least one of the feed gas flow or the oxidant gas flow establishing an axial gas flow through the inner wall and to the combustor, a mix zone downstream of the channel and the passage wherein the oxidant gas flow and feed gas flow mix, a flow conditioner disposed within said axial gas flow downstream of the mix zone, said flow conditioner including an elongated body having a length, an upstream end, a downstream end, an exterior surface at least partially disposed within the inner wall, and an interior passage for passage of said axial gas flow, the interior passage extending along the length, opening into the upstream and downstream ends and including an interior diameter, the interior diameter substantially smoothly reducing and then increasing from the upstream end to the downstream end, wherein the exterior surface of the flow conditioner includes a plurality of vanes, the vanes and the inner wall defining at least one substantially longitudinally extending channel for passage of said axial gas flow.