A gas turbine engine comprising: a fan section including a fan having a row of blades extending in a radial direction between a 0% span position at a hub and a 100% span position at a tip, wherein the hub is rotatable about an engine longitudinal axis such that the row of blades deliver flow to a bypass flow path, an intermediate flow path and a core flow path; a compressor section establishing the core flow path; a turbine section that drives the fan section and the compressor section; a fan case including a bypass duct surrounding the row of blades to establish the bypass flow path; a housing including a first flow splitter that divides flow between the bypass flow path and a second duct; a row of guide vanes in the bypass duct that extend in the radial direction across the bypass flow path; an engine case including a second flow splitter radially inboard of the first flow splitter and that divides flow from the second duct between the intermediate flow path and the core flow path; a bypass port that interconnects the intermediate and bypass flow paths (I, B) at a position downstream of the row of guide vanes; and one or more blocker doors situated in the intermediate flow path downstream of the bypass port, wherein the one or more blocker doors are moveable to selectively communicate flow in the intermediate flow path to a vent port; wherein each of the blades extends in the radial direction between the 0% span position and 100% span position to establish a hub-to-tip ratio, and the hub-to-tip ratio is less than or equal to 0.4 measured relative to a forwardmost portion of a leading edge of the blades, and wherein a forwardmost edge of the second flow splitter is axially aft of a forwardmost edge of the first flow splitter with respect to the engine longitudinal axis, and the forwardmost edges of the first and second flow splitters (170, 172) are axially forward of the row of guide vanes with respect to the engine longitudinal axis. a fan section including a fan having a row of blades extending in a radial direction between a 0% span position at a hub and a 100% span position at a tip, wherein the hub is rotatable about an engine longitudinal axis such that the row of blades deliver flow to a bypass flow path, an intermediate flow path and a core flow path; a compressor section establishing the core flow path; a turbine section that drives the fan section and the compressor section; a fan case including a bypass duct surrounding the row of blades to establish the bypass flow path; a housing including a first flow splitter that divides flow between the bypass flow path and a second duct; a row of guide vanes in the bypass duct that extend in the radial direction across the bypass flow path; an engine case including a second flow splitter radially inboard of the first flow splitter and that divides flow from the second duct between the intermediate flow path and the core flow path; a bypass port that interconnects the intermediate and bypass flow paths (I, B) at a position downstream of the row of guide vanes; and one or more blocker doors situated in the intermediate flow path downstream of the bypass port, wherein the one or more blocker doors are moveable to selectively communicate flow in the intermediate flow path to a vent port; wherein each of the blades extends in the radial direction between the 0% span position and 100% span position to establish a hub-to-tip ratio, and the hub-to-tip ratio is less than or equal to 0.4 measured relative to a forwardmost portion of a leading edge of the blades, and wherein a forwardmost edge of the second flow splitter is axially aft of a forwardmost edge of the first flow splitter with respect to the engine longitudinal axis, and the forwardmost edges of the first and second flow splitters (170, 172) are axially forward of the row of guide vanes with respect to the engine longitudinal axis.