Patent ID: 9388739
Filing Date: 2016-07-12
CPC Classification: F01D,F02C,F05D,Y02T

Claim Text:
1. An air cooler system for a gas turbine engine, comprising: an air cooler receiving a compressor air flow to pass therethrough, the air cooler disposed in an annular bypass air duct of the engine, the air cooler having an inlet opening to direct a flow of bypass air to the air cooler and an exit to direct exhaust air to the bypass air duct, the air cooler radially extending only part way into the bypass air duct to dispose a radial outer, side of the cooler spaced apart from an outer wall of the bypass duct, a front wedge having a radial central front edge circumferentially aligned with the inlet opening, the front wedge being disposed between the inlet opening and a radial inner edge of the cooler, and the front wedge being shaped to split air flow passing by the radial central front edge and to direct the split airflow around the air cooler to increase inlet pressure; wherein the radial central front edge extends radially inwardly from an annular edge of the inlet opening and wedge surfaces extend divergently from the radial central front edge of the wedge; and wherein the inlet opening is elliptical, defining a short central axis and a long central axis perpendicular to each other, an extension of the long central axis substantially superposing the radial central front edge of the front wedge.