Patent ID: 8033119
Filing Date: 2011-10-11
Classification: F01D,F05D,F23R

Abstract:
1. A transition member between a combustion section and a turbine section in a gas turbine engine, the transition member comprising: a casing inner wall having a forward end defining a combustion gas inlet downstream of the combustion section and an aft end axially spaced from said forward end and defining a combustion gas outlet upstream of the turbine section, said casing inner wall including a radially inner surface and an opposed radially outer surface, said radially inner surface defining an inner volume of the transition member therein; an impingement member disposed radially outwardly about said casing inner wall and spaced from said casing inner wall such that a first cooling fluid channel is formed between said impingement member and said casing inner wall, said impingement member including a plurality of apertures formed therein for effecting a passage of cooling fluid from an area radially outward of said impingement member to said first cooling fluid channel; and a plurality of spanning members extending from said radially outer surface of said casing inner wall into a pocket of said impingement member, said spanning members each including a slot formed therein having a component in the radial direction, said slot in communication with a first aperture formed in said radially inner surface of said inner wall and at least one second aperture formed in said spanning member for effecting a passage of said cooling fluid from said first cooling fluid channel to said inner volume defined within said radially inner surface of said casing inner wall.