A gas turbine engine (10) includes a nacelle (24) defining a centerline axis (A) and an annular splitter (30) radially inward from the nacelle. A spinner (32) is radially inward of the nacelle forward of a compressor section (14). A fan blade (36) extends from a fan blade platform (34). A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H is the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio of for reducing foreign object debris (FOD) intake into the compressor section.
Nacelle and compressor inlet arrangements
2018-08-21
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke |