Patent ID: 7574865
Filing Date: 2009-08-18
Classification: F05B,F23R

Abstract:
1. A combustor for a turbine engine comprising: a combustor head-end; a liner extending from the head-end; a flow sleeve having an axial upstream end and an axial downstream end, the downstream end of the flow sleeve being secured to the combustor head-end, at least a portion of the liner extending into the flow sleeve, wherein a substantially annular flow passage to the head-end is defined therebetween, the flow passage having an axial inlet formed between the axial upstream end of the flow sleeve and the liner; wherein the flow sleeve includes a plurality of openings distributed about the flow sleeve in a region defined between the axial downstream end and an axially central location of the flow sleeve, the openings permitting fluid communication between the exterior of the flow sleeve and the flow passage, whereby an uneven distribution of the flow into the head-end through the passage is made substantially uniform.