Patent ID: 7805946
Filing Date: 2010-10-05
Classification: F23R

Abstract:
1. A turbine engine combustor system comprising: a combustor component; a substantially tubular flow sleeve having an axial upstream end, an axial downstream end and an outer peripheral surface, the downstream end being substantially tubular without a flange extending radially outwardly from the outer peripheral surface, the downstream end of the flow sleeve being connected to the combustor component by a plurality of fasteners such that the outer peripheral surface of the flow sleeve and the combustor component are in direct contact circumferentially about at least a portion of the outer peripheral surface of the flow sleeve, the flow sleeve extending cantilevered from the combustor component to the upstream end, whereby the upstream end of the flow sleeve is not attached to another structure, the flow sleeve having a longitudinal axis, the fasteners extending substantially radially to the longitudinal axis.