Patent ID: 9638103
Date: 2017-05-02
CPC Classifications: F02C,F05D

Claim:
1. A gas turbine engine, comprising: a compressor section, a combustion section, and turbine section disposed in flow series, the compressor section having an air inlet; and an inlet particle separator system coupled to, and disposed upstream of, the compressor section, the inlet particle separator system, comprising: a hub section; a shroud section surrounding at least a portion of the hub section and spaced apart therefrom to define a passageway, the passageway having an air inlet; a splitter disposed downstream of the air inlet and extending into the passageway to divide the passageway into a scavenge flow path and an engine flow path; and a plasma flow control actuator coupled to the hub section and disposed between the air inlet and the splitter, wherein the engine has an engine centerline, and wherein: the hub section is symmetrically disposed about the engine centerline, and includes an inlet portion, an outlet portion, and a transition portion disposed between the inlet and outlet portions: the inlet portion is defined by a first surface having a first maximum angle at a first point, the first maximum angle relative to the engine centerline: the outlet portion is defined by a second surface having a second maximum angle at a second point the second maximum angle relative to the engine centerline; and the transition portion is defined by a third surface having a curvature that defines a hub turning angle, the hub turning angle defined as a symmetric arc that subtends a first line and a second line; the first line is a line that extends through the first point at the first maximum angle; and the second line is a line that extends through the second point at the second maximum angle, the first maximum angle is greater than 30-degrees, and the symmetric arc is greater than 280-degrees.