Variable pitch fans for turbomachinery engines
AssigneeGeneral Electric Company
InventorsDaniel A. Niergarth, Martin Manning, Nicholas M. Daggett, Christopher J. Kroger, Ian F. Prentice
Life of this patent
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Abstract
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/in2 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.
Claims20
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/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 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.
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/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 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.
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/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 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.
Dependencies are inferred from the claim text.