Patent ID: 9322556
Filing Date: 2016-04-26
CPC Classification: F01D,F23R

Claim Text:
1. A flow sleeve assembly for a combustor of a gas turbine, comprising: a. an annular support sleeve disposed at a forward end of the flow sleeve assembly, the support sleeve having a forward portion axially separated from an aft portion, wherein the support sleeve includes an annular flange having an axial length, the flange extending circumferentially around the forward portion of the support sleeve, the flange being positioned concentrically within a fuel distribution manifold such that the flange slides along an inner side portion of the fuel distribution manifold during operation of the combustion module; b. an aft frame disposed at an aft end of the flow sleeve assembly; c. an annular flow sleeve that extends from the aft portion of the support sleeve towards the aft frame, the flow sleeve having a forward end axially separated from an aft end, the forward end of the flow sleeve circumferentially surrounding the aft portion of the support sleeve; and d. an annular impingement sleeve that extends between the aft end of the flow sleeve and the aft frame, the impingement sleeve having a forward end that is connected to the aft end of the flow sleeve and an aft end that is connected to the aft frame.