US 12,085,026 B2
Overall engine efficiency rating for turbomachine engines
Andrea Piazza, Rivalta di Torino (IT); and Jeffrey D. Clements, Evendale, OH (US)
Assigned to GE Avio S.r.l., (IT); and General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US); and GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Mar. 14, 2024, as Appl. No. 18/604,985.
Application 18/604,985 is a continuation of application No. 18/209,689, filed on Jun. 14, 2023.
Application 18/209,689 is a continuation of application No. 17/929,542, filed on Sep. 2, 2022, granted, now 11,713,721, issued on Aug. 1, 2023.
Application 17/929,542 is a continuation of application No. 17/694,444, filed on Mar. 14, 2022, granted, now 11,466,624, issued on Oct. 11, 2022.
Claims priority of application No. 102022000001613 (IT), filed on Jan. 31, 2022.
Prior Publication US 2024/0254925 A1, Aug. 1, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F02C 3/067 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 3/067 (2013.01); F02K 3/06 (2013.01); F05D 2200/13 (2013.01); F05D 2200/14 (2013.01); F05D 2200/221 (2013.01); F05D 2260/40311 (2013.01); F05D 2260/98 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbomachine engine comprising:
a fan assembly including a plurality of fan blades;
a vane assembly including a plurality of vanes disposed aft of the plurality of fan blades;
a core engine including a low-pressure turbine;
a gearbox including an input, an output, and a gear ratio (GR), wherein the input of the gearbox is coupled to the low-pressure turbine of the core engine, wherein the output of the gearbox is coupled to the fan assembly, and wherein the GR is within a range of 2.0-4.0; and
an overall engine efficiency rating greater than or equal to 1.9 and less than or equal to GR1.5, wherein the overall engine efficiency rating equals

OG Complex Work Unit Math
 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 is within a range of 72-216 inches, wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition, and wherein N is a number of rotating blade stages of the low-pressure turbine.