Patent ID: 7565803
Filing Date: 2009-07-28
Classification: F23R,Y02T

Abstract:
1. A swirler arrangement for a mixing assembly of a gas turbine engine combustor, said swirler arrangement having a centerline axis therethrough, comprising: (a) a swirler housing including an outer radial wall and an upstream wall; (b) a first plurality of vanes incorperated into said outer radial wall, wherein said first plurality of vanes are oriented at a first angle with respect to an axis through said outer radial wall; and, (c) a second plurality of vanes incorporated into said outer radial wall, wherein said second plurality of vanes are oriented at a second angle with respect to said axis through said outer radial wall different from said first angle; wherein a first type of passage is defined between adjacent first and second vanes having a first configuration converging from an upstream end to a downstream end and a second type of passage is defined between adjacent first and second vanes having a second configuration diverging from an upstream end to a downstream end so that air flowing through said swirler arrangement is swirled in a desirable manner.