Patent ID: 11933190
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 4:
5. The gas turbine engine as set forth in claim 2, wherein a first gap is defined between a leading edge of the fan exit guide vanes at a radially innermost point radially outward of the splitter wall and a leading edge of the plurality of rigid mounts at a radially inner location radially inward of the splitter wall, and a second gap is defined between a trailing edge of the fan blades and a leading edge of the plurality of fan exit guide vanes at the radially inward point radially outward of the splitter wall each of the gaps being defined by extending a line from the respective points in a radially outward direction, and then measuring a distance with a line extending parallel to the rotational axis of the engine, and a first gap ratio of said second gap to said first gap is between 0.25 and 0.45.