Turbomachinery engines with high-speed low-pressure turbines
AssigneeGeneral Electric Company
InventorsPranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Abstract
A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes four rotating stages. The low-pressure turbine includes 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. In some instances, the area ratio is within a range of 2.0-5.1. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.
Claims7
A turbomachinery engine comprising:
- a fan assembly comprising a plurality of fan blades, wherein the fan assembly comprises a diameter within a range of 78-84 inches;
- a low-pressure compressor comprising exactly three stages;
- a high-pressure compressor comprising exactly nine-8-11 stages;
- a combustor;
- a high-pressure turbine comprising exactly two stages;
- a low-pressure turbine comprising 3-4 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 2.0-5.1;
- and
- 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, wherein the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and wherein a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.0-3.3.
A turbomachinery engine comprising:
- a fan assembly comprising exactly 20 fan blades, wherein the fan assembly comprises a diameter within a range of 78-84 inches;
- a low-pressure compressor comprising exactly three stages;
- a high-pressure compressor comprising exactly nine stages;
- a combustor;
- a high-pressure turbine comprising exactly two stages;
- a low-pressure turbine comprising exactly four 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 2.55-2.65;
- and
- 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, wherein the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and wherein a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.0-3.3.
Dependencies are inferred from the claim text.