Patent ID: 7254937
Filing Date: 2007-08-14
Classification: F02C,F28D

Abstract:
1. A heat exchanger assembly for a gas turbine engine, said heat exchanger assembly comprising: an annular manifold comprising an inlet manifold coupled in flow communication with a compressor and an outlet manifold coupled in flow communication with a combustor, said annular manifold substantially concentrically aligned with respect to an axis of rotation of the gas turbine engine, and said inlet manifold and said outlet manifold adjoining each other and each including an outermost surface having a substantially equal radial distance with respect to the axis of rotation of the gas turbine engine; and an annular heat exchanger coupled in flow communication to the compressor via said annular manifold, said heat exchanger configured to channel compressor discharge air to a said combustor, said heat exchanger assembly coupled to said gas turbine engine such that said heat exchanger is substantially concentrically aligned with respect to the axis of rotation of the gas turbine engine, said heat exchanger comprising a plurality of heat exchanger elements, wherein each heat exchanger element is aligned substantially perpendicular to a direction of exhaust flow discharged substantially axially from the gas turbine engine.