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 a plurality of 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 plurality of 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 , wherein the first VPF parameter is within a range of 0.20 to 0.40.
3. The turbomachinery engine of claim 1 , wherein the first VPF parameter is within a range of 0.15 to 0.30.
4. The turbomachinery engine of claim 1 , wherein the second VPF parameter is within a range of 2-30 lbf/in 2 .
5. The turbomachinery engine of claim 1 , wherein the second VPF parameter is within a range of 1-5.25 lbf/in 2 .
6. The turbomachinery engine of claim 1 , wherein the second VPF parameter is within a range of 2-5.25 lbf/in 2 .
7. The turbomachinery engine of claim 1 , further comprising a pitch change mechanism coupled to the plurality of variable pitch fan blades and configured for adjusting a pitch of the plurality of variable pitch fan blades.
8. A turbomachinery engine comprising:
a fan assembly including a plurality of 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 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.
9. The turbomachinery engine of claim 8 , further comprising a pitch change mechanism coupled to the plurality of variable pitch fan blades and configured for adjusting a pitch of the plurality of variable pitch fan blades.
10. The turbomachinery engine of claim 9 , wherein the pitch change mechanism comprises at least one of a linear motion pitch change mechanism, a rotatory motion pitch change mechanism, a hydraulically driven pitch change mechanism, or an electrically driven pitch change mechanism.
11. The turbomachinery engine of claim 10 , wherein the pitch change mechanism is disposed on an engine centerline axis.
12. The turbomachinery engine of claim 10 , wherein the pitch change mechanism is offset from an engine centerline axis.
13. The turbomachinery engine of claim 8 , wherein the first VPF parameter is within a range of 0.20 to 0.40.
14. The turbomachinery engine of claim 8 , wherein the first VPF parameter is within a range of 0.10 to 0.30.
15. The turbomachinery engine of claim 8 , wherein the first VPF parameter is within a range of 0.15 to 0.30.
16. The turbomachinery engine of claim 8 , wherein the first VPF parameter is within a range of 0.10 to 0.25.
17. A turbomachinery engine comprising:
a fan assembly including a plurality of 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 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.
18. The turbomachinery engine of claim 17 , wherein the fan assembly is disposed within a fan case, wherein the first VPF parameter is within a range of 0.2-0.36, and wherein the second VPF parameter is within a range of 5-27 lbf/in 2 .
19. The turbomachinery engine of claim 17 , wherein the fan assembly is an unducted fan assembly, and wherein the second VPF parameter is within a range of 2-4.6 lbf/in 2 .
20. The turbomachinery engine of claim 17 , further comprising a pitch change mechanism coupled to the plurality of variable pitch fan blades and configured for adjusting a pitch of the plurality of variable pitch fan blades, and wherein the pitch change mechanism comprises at least one of a linear motion pitch change mechanism, a rotatory motion pitch change mechanism, a hydraulically driven pitch change mechanism, or an electrically driven pitch change mechanism.