Patent ID: 7600370

Claim:
A mid-frame section of a gas turbine engine comprising: a plenum, in fluid communication with an aft end of an annular diffuser, the plenum comprising a confined annular space defined exteriorly by a casing and inboardly by an annular wall and in which are disposed a plurality of combustion chambers, connected in parallel with respect to a fluid flow from the annular diffuser during operation, and a plurality of transitions each respectively coupled to one of said combustion chambers, for directing the fluid flow to a respective turbine inlet opening; a first annular flow splitter comprising a leading edge, a trailing edge, an upstream surface and a downstream surface, and spaced from the annular wall by a first height, the first height effective to partition a first portion of the fluid flow directed with a radial component along the upstream surface of the first annular flow splitter from a second portion of fluid flow continuing substantially axially from the annular diffuser; and a second annular flow splitter, in the plenum, comprising a leading edge spaced aft of the annular diffuser aft end, a trailing edge, an upstream surface and a downstream surface, and spaced from the annular wall by a second height, the second height effective to partition the second portion into a third portion of fluid flow directed with a radial component along the upstream surface of the second annular flow splitter from a fourth portion of fluid flow continuing substantially axially, wherein the first and the second annular flow splitters are configured to provide a diffusion effect beyond that of the annular diffuser.