Variable pitch fans for turbomachinery engines
A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in 2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.
1 . A turbomachinery engine comprising:
a fan assembly including 8-26 variable pitch fan blades, a first VPF parameter, and a second VPF parameter, wherein:
the first VPF parameter is within a range of 0.10-0.40 and is defined by a fan blade radius ratio (RR) divided by a fan pressure ratio (FPR) at a static sea-level takeoff operating condition; and
the second VPF parameter is within a range of 1-30 lbf/in 2 and is defined by a bearing spanwise force (F_Span) at a redline operating condition measured in pounds force divided by a fan area (F_Area) measured in square inches;
a vane assembly including a plurality of vanes disposed aft of the variable pitch fan blades;
a core engine including one or more turbine sections; and
a gearbox including an input and an output, wherein the input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, wherein the output is coupled to the fan assembly and has a second rotational speed which is less than the first rotational speed.
2 . The turbomachinery engine of claim 1 , comprising 12-20 variable pitch fan blades.
3 . The turbomachinery engine of claim 1 , comprising exactly 12 variable pitch fan blades.
4 . The turbomachinery engine of claim 1 , comprising exactly 14 variable pitch fan blades.
5 . The turbomachinery engine of claim 1 , comprising exactly 16 variable pitch fan blades.
6 . The turbomachinery engine of claim 1 , comprising exactly 18 variable pitch fan blades.
7 . The turbomachinery engine of claim 1 , comprising exactly 20 variable pitch fan blades.
8 . The turbomachinery engine of claim 1 , comprising exactly 22 variable pitch fan blades.
9 . The turbomachinery engine of claim 1 , comprising exactly 24 variable pitch fan blades.
10 . The turbomachinery engine of claim 1 , wherein the one or more turbine sections of the core engine comprises a high-pressure turbine comprising 1-2 stages and a low-pressure turbine comprising 3-6 stages.
11 . The turbomachinery engine of claim 1 , wherein the core engine further comprises one or more compressor sections, wherein the one or more compressor sections of the core engine comprises a low-pressure compressor having 3-5 stages and a high-pressure compressor comprising 9-10 stages, and wherein the one or more turbine sections of the core engine comprises a high-pressure turbine comprising 2 stages and a low-pressure turbine comprising 3-4 stages.
12 . A turbomachinery engine comprising:
a fan assembly including 8-26 variable pitch fan blades, a first VPF parameter, and a second VPF parameter, wherein:
the first VPF parameter is within a range of 0.10-0.40 and is defined by a fan blade radius ratio (RR) divided by a fan pressure ratio (FPR) at a static sea-level takeoff operating condition; and
the second VPF parameter is within a range of 1.0-5.25 lbf/in 2 and is defined by a bearing spanwise force (F_Span) at a redline operating condition measured in pounds force divided by a fan area (F_Area) measured in square inches;
a core engine including one or more compressor sections and one or more turbine sections; and
a gearbox including an input and an output, wherein the input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, wherein the output is coupled to the fan assembly and has a second rotational speed which is less than the first rotational speed.
13 . The turbomachinery engine of claim 12 , wherein the first VPF parameter is within a range of 0.20 to 0.40.
14 . The turbomachinery engine of claim 12 , wherein the first VPF parameter is within a range of 0.10 to 0.30.
15 . The turbomachinery engine of claim 12 , wherein the first VPF parameter is within a range of 0.15 to 0.30.
16 . The turbomachinery engine of claim 12 , wherein the first VPF parameter is within a range of 0.10 to 0.25.
17 . The turbomachinery engine of claim 12 , wherein the one or more turbine sections of the core engine comprises a high-pressure turbine comprising exactly 2 stages and a low-pressure turbine comprising exactly 3 stages.
18 . The turbomachinery engine of claim 12 , wherein the one or more turbine sections of the core engine comprises a high-pressure turbine comprising exactly 2 stages and a low-pressure turbine comprising exactly 4 stages.
19 . The turbomachinery engine of claim 12 , wherein the one or more compressor sections of the core engine comprises a high-pressure compressor comprising exactly 8-11 stages.
20 . A turbomachinery engine comprising:
a fan assembly including 8-26 variable pitch fan blades, a first VPF parameter, and a second VPF parameter, wherein:
the first VPF parameter is within a range of 0.15-0.39 and is defined by a fan blade radius ratio (RR) divided by a fan pressure ratio (FPR) at a static sea-level takeoff operating condition; and
the second VPF parameter is within a range of 2-27 lbf/in 2 and is defined by a bearing spanwise force (F_Span) at a redline operating condition measured in pounds force divided by a fan area (F_Area) measured in square inches;
a core engine including one or more compressor sections and one or more turbine sections; and
a gearbox including an input and an output, wherein the input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, wherein the output is coupled to the fan assembly and has a second rotational speed which is less than the first rotational speed.