Patent ID: 11873738
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 6:
7. A fan section of a gas turbine engine, comprising:
an array of fan blades;
an array of fan exit stators, each of the fan exit stators including a first airfoil including a first leading edge and a first trailing edge, the fan exit stators positioned upstream of a compressor of the gas turbine engine and within a cross-sectional area of a turbine casing;
an array of second airfoils downstream of the array of fan exit stators, each of the second airfoils including a second leading edge and a second trailing edge, the array of second airfoils defining a row adjacent to at least a portion of the fan exit stators;
a plurality of fan frame struts, each of the fan frame struts including a third leading edge and a third trailing edge, the third leading edge of each of the fan frame struts aerodynamically integrated into the first trailing edge of a first portion of the fan exit stators, the third trailing edge of each of the fan frame struts separated from the second leading edge of the second airfoils in an axial direction defined by the gas turbine engine downstream of the third trailing edge; and
an adhesive between the third leading edge and the first trailing edge, a portion of the fan exit stator to separate the adhesive from a pressure surface and a suction surface defined between the first leading edge and the third trailing edge.