Counter-rotating gearbox for tip turbine engine
A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.
1. A method of operating a turbine engine including the steps of:
rotatably driving a fan having a plurality of hollow fan blades with a turbine mounted to an outer periphery of the fan, wherein the turbine includes turbine blades disposed radially outward of the plurality of hollow fan blades; and
counter-rotatably driving an axial compressor rotor via rotation of the fan, wherein the axial compressor rotor is counter-rotatably driven by a planetary gearset that couples the fan to the axial compressor rotor.
2. The method of claim 1 further including the step of compressing air with the axial compressor rotor and guiding the compressed air radially outwardly through interiors of the plurality of fan blades toward the turbine.
3. The method of claim 2 further including the step of centrifugally compressing the compressed air in the interiors of the plurality of fan blades.
4. The method of claim 1 wherein a rate at which the axial compressor rotor is driven is higher than a rate of rotation of the fan.
5. The method of claim 4 , wherein the ratio of the rate at which the axial compressor rotor is driven to the rate of rotation of the fan is 3.34-to-1.
6. The method of claim 1 further including the step of coupling the axial compressor rotor to a sun gear of the planetary gearset.
7. The method of claim 6 further including the step of coupling a planet carrier of the planetary gearset with the fan, the planetary gearset including a first planet gear engaging the sun gear and a second planet gear engaging the first planet gear, at least one of the first planet gear and the second planet gear mounted to the planet carrier.
8. The method of claim 1 , wherein an axial compressor corresponding to the axial compressor rotor comprises at least one stationary compressor vane.
9. The method of claim 1 , wherein the planetary gearset is aft of the fan and the turbine.
10. The method of claim 1 , wherein an axial compressor corresponding to the axial compressor rotor only includes a plurality of compressor blades that are counter-rotatably driven relative to the plurality of fan blades.
11. A method of operating a turbine engine including the steps of:
rotatably driving a fan having a plurality of fan blades with a turbine mounted at an outer periphery of the fan; and
counter-rotatably driving an axial compressor rotor via rotation of the fan, wherein the axial compressor rotor is counter-rotatably driven by a planetary gearset that couples the fan to the axial compressor rotor, wherein an axial compressor corresponding to the axial compressor rotor comprises at least one stationary compressor vane between two of a plurality of compressor blades.
12. The method of claim 11 further including the step of compressing air with the axial compressor rotor and guiding the compressed air radially outwardly through interiors of the plurality of fan blades toward the turbine.
13. The method of claim 11 further including the step of coupling the axial compressor rotor to a sun gear of the planetary gearset.
14. The method of claim 13 further including the step of coupling a planet carrier of the planetary gearset with the fan, the planetary gearset including a first planet gear engaging the sun gear and a second planet gear engaging the first planet gear, at least one of the first planet gear and the second planet gear mounted to the planet carrier.
15. The method of claim 11 , wherein the planetary gearset is aft of the fan and the turbine.
16. The method of claim 11 , wherein the ratio of a rate at which the axial compressor rotor is driven to the rate of rotation of the fan is 3.34-to-1.
17. The method of claim 11 , wherein an axial compressor corresponding to the axial compressor rotor only includes a plurality of compressor blades that are counter-rotatably driven relative to the plurality of fan blades.