Patent ID: 7685823
Filing Date: 2010-03-30
Classification: F01D,F23R

Abstract:
1. A gas turbine combustor having increased combustion stability, said combustor comprising: A flow sleeve having a first end, a second end, and a plurality of first holes in a plurality of axially spaced rows located proximate said second end; A combustion liner located radially within said flow sleeve thereby forming a first passage therebetween; At least one fuel nozzle for injecting a fuel to mix with air in said combustion liner; and, A plurality of vanes, said vanes fixed to said flow sleeve proximate said plurality of first holes and extending radially inward towards said combustion liner into said first passage such that said plurality of vanes significantly remove the tangential velocity component from air entering said first passage through said plurality of first holes, thereby directing said air in a substantially axial direction towards said flow sleeve first end, wherein said plurality of vanes are equal in number to a quantity of first holes in a row and wherein said vanes are circumferentially offset from said holes in at least one of said axially spaced rows while bisecting remaining holes in said flow sleeve.