US 11,852,161 B1
Turbomachine and method of assembly
Jixian Yao, Niskayuna, NY (US); Trevor H. Wood, Clifton Park, NY (US); Kishore Ramakrishnan, Rexford, NY (US); William J. Solomon, Montgomery, OH (US); Giridhar Jothiprasad, Clifton Park, NY (US); and Aaron J. King, West Harrison, IN (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Apr. 24, 2023, as Appl. No. 18/138,442.
Application 18/138,442 is a continuation in part of application No. 17/986,544, filed on Nov. 14, 2022, granted, now 11,661,851.
Int. Cl. F01D 5/14 (2006.01); F04D 29/38 (2006.01); F04D 19/00 (2006.01)
CPC F04D 29/384 (2013.01) [F04D 19/002 (2013.01)] 25 Claims
OG exemplary drawing
 
1. A turbomachine for an aircraft comprising:
an annular casing; and
a fan disposed inside the annular casing and mounted for rotation about an axial centerline, the fan including fan blades that extend radially outwardly toward the annular casing;
wherein the fan includes an average fan chord width of the fan blades (“c”), a diameter of the fan (“D”), a fan pressure ratio (“FPR”), and a redline corrected fan tip Mach number (“Mtip,c(RL)”) according to a First Performance Factor (“FPF”),
wherein

OG Complex Work Unit Math
wherein m1·[Mtip,c(RL)−1.1]+6>FPF>m1·[Mtip,c(RL)−1.1]+Δy1, and
wherein 0<Δy1<6.