US 12,140,082 B2
Turbomachinery engines with high-speed low-pressure turbines
Pranav R. Kamat, Bengaluru (IN); Bhaskar Nanda Mondal, Bengaluru (IN); and Jeffrey D. Clements, Evendale, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 1, 2024, as Appl. No. 18/652,436.
Application 18/652,436 is a continuation of application No. 18/318,604, filed on May 16, 2023, granted, now 12,012,901.
Claims priority of application No. 202311010789 (IN), filed on Feb. 17, 2023.
Prior Publication US 2024/0287941 A1, Aug. 29, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F01D 1/26 (2006.01); F02C 3/06 (2006.01); F02K 3/06 (2006.01); F02K 3/077 (2006.01)
CPC F02C 7/36 (2013.01) [F01D 1/26 (2013.01); F02C 3/06 (2013.01); F02K 3/06 (2013.01); F02K 3/077 (2013.01); F05D 2220/325 (2013.01); F05D 2260/4031 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbomachinery engine comprising:
an unducted fan assembly including a plurality of fan blades;
a core engine including a compressor section, a combustion section, and a turbine section, wherein the core engine is encased in a core casing comprising a core diameter (Dcore) at a maximum extent of the core casing, wherein the turbine section includes a low-pressure turbine comprising exactly 4 rotating stages, wherein each rotating stage of the low-pressure turbine comprises an annular exit area defined by a tip radius of a trailing edge of any one blade of the rotating stage and a hub radius of the any one blade of the rotating stage at an axial location aligned with the tip radius, wherein the low-pressure turbine comprises an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine, and wherein the area ratio is within a range of 3.1-5.1;
a gearbox including an input and an output, wherein the input of the gearbox is coupled to the low-pressure turbine and comprises a first rotational speed, and wherein the output of the gearbox is coupled to the fan assembly and comprises a second rotational speed; and
a length (L) from a longitudinally forward end of the turbomachinery engine to a longitudinally aft end of the turbomachinery engine, wherein a ratio of L to Dcore is within a range of 2-5.