Gas turbine engine with core debris protection

A gas turbine engine comprising:

• a fan having a plurality of fan blades received within a fan case, said fan rotating with a rotating cone;
• the fan delivering air into a bypass duct radially outwardly of a core splitter housing having a leading edge, and radially inwardly of the core splitter housing into a core engine path leading to a compressor section;
• the rotating cone having a rotating bulge defining a radially outermost point of the rotating cone relative to a rotational axis of the fan blades and cone, the rotating bulge defined by a radially outwardly extending forward portion leading to the radially outermost point on the bulge and then a radially inwardly extending portion aft of the radially outermost point of the bulge leading into the core engine path within the core splitter housing, and the bulge radially outermost point being upstream of the leading edge of the core splitter housing, the bulge radially outermost point being a first radial distance from a rotational axis, and the leading edge of the core splitter housing being at a second radial distance of the rotational axis, and a ratio of the first radial distance to the second radial distance being at least 0.95;
• and
• wherein the variable inlet guide vane is not covered radially outward of the variable inlet guide vane.

A gas turbine engine comprising:

• a fan having a plurality of fan blades received within a fan case, said fan rotating with a rotating cone;
• the fan delivering air into a bypass duct radially outwardly of a core splitter housing having a leading edge, and radially inwardly of the core splitter housing into a core engine path leading to a compressor section;
• the rotating cone having a rotating bulge defining a radially outermost point of the rotating cone relative to a rotational axis of the fan blades and cone, the rotating bulge defined by a radially outwardly extending forward portion leading to the radially outermost point on the bulge and then a radially inwardly extending portion aft of the radially outermost point of the bulge leading into the core engine path within the core splitter housing, and the bulge radially outermost point being upstream of the leading edge of the core splitter housing, the bulge radially outermost point being a first radial distance from a rotational axis, and the leading edge of the core splitter housing being at a second radial distance of the rotational axis, and a ratio of the first radial distance to the second radial distance being at least 0.95;
• and
• wherein a dirt flap is positioned within the core engine path, and there being a compressor section downstream of the core splitter housing, with the dirt flap being positioned upstream of the compressor section.