CPC F02C 7/36 (2013.01) [F01D 17/162 (2013.01); F02C 7/06 (2013.01); F05D 2200/13 (2013.01); F05D 2200/14 (2013.01); F05D 2200/22 (2013.01); F05D 2220/323 (2013.01); F05D 2260/40311 (2013.01); F05D 2260/98 (2013.01)] | 20 Claims |
1. A turbomachine engine comprising:
a fan case;
a fan assembly disposed radially within the fan case and comprising a plurality of fan blades;
a core engine including a low-pressure turbine;
a vane assembly including a plurality of vanes, wherein the vanes are disposed aft of the fan blades and are coupled to the core engine and the fan case;
a gearbox coupled to the low-pressure turbine and the fan assembly, wherein the gearbox comprises a gear ratio within a range of 4.1-5.36; and
a gearbox efficiency rating of 0.21-0.33, wherein the gearbox efficiency rating equals
wherein Q is a gearbox oil flow rate at an inlet of the gearbox measured in gallons per minute at a max takeoff condition, wherein D is a diameter of the fan blades measured in inches, and wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition.
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