General Electric Company
Protected core inlet with reduced capture area

Abstract:

A gas turbine engine defines a radial direction and an axial centerline. The gas turbine engine includes a core turbine engine that defines a core inlet. The core inlet is oriented with respect to the axial centerline and positioned along the radial direction such that the area available to capture foreign object debris is minimized. In one aspect, the gas turbine engine defines a capture ratio less than about 35%, wherein the capture ratio is a ratio of an area between a splitter radius and a tangency radius to an area encompassed by the splitter radius. The splitter radius is defined as a radial distance between the axial centerline and an outer lip of a splitter of the core turbine engine. The tangency radius is defined as a radial distance between the axial centerline and a tangency point, which can be defined at an inner lip of the core inlet.