Patent ID: 8646276
Filing Date: 2014-02-11
Classification: F23R

Abstract:
1. A combustor for a turbine engine, comprising: a combustor liner; an end cap mounted at an upstream end of the combustor liner; and a flow sleeve that surrounds an exterior of the combustor liner, wherein compressed air flows through an annular space between an outer surface of the combustor liner and an inner surface of the flow sleeve, wherein cooling holes penetrate the flow sleeve, the cooling holes allowing compressed air to flow from an exterior of the flow sleeve into the annular space, and wherein the flow sleeve includes at least one reduced diameter portion, a height of the annular space being smaller along the at least one reduced diameter portion of the flow sleeve than along other portions of the flow sleeve, wherein a diameter of the cooling holes along the at least one reduced diameter portion of the flow sleeve is greater than a diameter of the cooling holes along the other portions of the flow sleeve.