Patent ID: 9085981
Filing Date: 2015-07-21
Classification: F01D,F05D,F23R

Abstract:
1. A ducting arrangement for a can annular gas turbine engine, comprising: a duct disposed between a combustor and a first row of turbine blades and defining a hot gas path therein, the duct comprising raised geometric features incorporated into a duct outer surface; a flow sleeve defining a cooling flow path between an inner surface of the flow sleeve and the duct outer surface; and a plurality of refresher cooling holes through the flow sleeve establishing fluid communication between a plenum surrounding the ducting arrangement and the cooling flow path; wherein the flow sleeve is configured to direct a flow of cooling fluid in the cooling flow path in a direction against a direction of a flow of a hot gas flowing in the hot gas path; wherein the raised geometric features comprise annular ribs oriented transverse to the direction of the flow of the cooling fluid in the cooling flow path, wherein after each time the flow of cooling fluid flows between the flow sleeve and a relatively upstream raised geometric feature, the inner surface of the flow sleeve deflects inward to direct the flow of cooling fluid toward a landing separating the relatively upstream raised geometric feature from a relatively downstream raised geometric feature, wherein the flow sleeve deflects outwards each time the flow sleeve is axially adjacent each of the raised geometric features, and wherein the inward and outward deflections repeat to form an undulation along a central axis of the hot gas path.