CPC F02K 3/06 (2013.01) [F02K 3/072 (2013.01); F04D 29/362 (2013.01); F01D 7/00 (2013.01); F02K 3/075 (2013.01); F02K 3/077 (2013.01); F05D 2220/36 (2013.01); F05D 2260/40311 (2013.01); F05D 2260/74 (2013.01)] | 20 Claims |
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/in2 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.
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