Patent ID: 8109720

Claim:
A system, comprising: a turbine engine comprising a radial diffuser disposed about a first axis downstream in an exhaust flow path from a turbine section; and an exhaust plenum, comprising: an inlet, wherein the radial diffuser is disposed through the inlet into the exhaust plenum, and the exhaust plenum extends along a second axis crosswise relative to the first axis of the turbine engine; a flow splitter extending completely across the exhaust plenum along the first axis, wherein the flow splitter extends in a first direction radially outward from the radial diffuser relative to the first axis, and the flow splitter bends from the first direction to a second direction downstream along the second axis; and a set of first and second aerodynamic surfaces facing one another about the radial diffuser, wherein the first and second aerodynamic surfaces are axially offset from one another by an axial offset along the first axis, and the first and second aerodynamic surfaces gradually expand the axial offset with increasing radial distance away from the first axis.