Counter-rotating gearbox for tip turbine engine
A tip turbine engine ( 10 ) provides an axial compressor rotor ( 46 ) that is counter-rotated relative to a fan ( 24 ). A planetary gearset ( 90 ) couples rotation of a fan ( 46 ) to an axial compressor rotor ( 46 ), such that the axial compressor rotor ( 46 ) 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 ( 54 ) between the final stage of compressor blades ( 52 ) and inlets ( 66 ) to the hollow fan blades ( 28 ) of the fan are eliminated. As a result, the length of the axial compressor ( 22 ) and the overall length of the tip turbine engine ( 10 ) are decreased.
1. A turbine engine comprising:
a fan rotatable about an axis, the fan including a plurality of fan blades;
a turbine having a plurality of turbine blades mounted at outer ends of the fan blades, the turbine rotatably driving the fan; and
an axial compressor rotor including at least one set of compressor blades, the axial compressor rotor driven in a rotational direction opposite that of the fan, wherein at least one gear couples the axial compressor rotor to the fan such that the axial compressor rotor is counter-rotatably driven by the fan.
2. The turbine engine of claim 1 wherein the at least one set of compressor blades of the axial compressor rotor includes a plurality of axially-spaced sets of compressor blades, each of the plurality of axially-spaced sets of compressor blades driven counter-rotationally by the rotation of the fan via the at least one gear.
3. The turbine engine of claim 1 wherein the at least one gear includes a sun gear and at least one planet gear.
4. The turbine engine of claim 3 wherein the at least one planet gear includes a first planet gear coupled to the sun gear and a second planet gear coupled to the first planet gear.
5. The turbine engine of claim 4 wherein the axial compressor rotor is coupled to the sun gear.
6. The turbine engine of claim 5 wherein the at least one gear further includes a planet carrier carrying the second planet gear, the planet carrier coupled to the fan.
7. The turbine engine of claim 1 , wherein at least one of the fan blades includes a compressor chamber extending radially therein and an inlet leading toward the compressor chamber, the compressor chamber and the inlet rotatable with the fan, the compressor chamber leading toward a combustor which generates a high-energy gas stream to drive the turbine, the axial compressor rotor compressing core airflow leading to the compressor chamber, the at least one set of compressor blades including a final stage of compressor blades immediately adjacent the inlet to the compressor chamber with no intervening compressor vanes.
8. A turbine engine comprising:
a fan rotatable about an axis, the fan including a plurality of fan blades;
a turbine having at least one turbine blade mounted at outer ends of the fan blades;
a planetary gearset including a sun gear, a first planet gear, a second planet gear, a planet carrier and a ring gear;
the sun gear engaging the first planet gear, the first planet gear engaging the second planet gear, at least one of the first planet gear and the second planet gear being carried by the planet carrier, the second planet gear engaging the ring gear; and
an axial compressor rotor having a plurality of compressor blades extending radially, the planetary gearset coupling the fan to the axial compressor rotor such that the axial compressor rotor is counter-rotationally driven by the fan.
9. The turbine engine of claim 8 wherein at least one fan blade of the plurality of fan blades defines a compressor chamber extending radially therein.
10. The turbine engine of claim 9 further including at least one combustor receiving core airflow from the compressor chamber, the at least one turbine mounted aft of the at least one combustor.
11. The turbine engine of claim 10 wherein the fan further includes an inlet leading toward the compressor chamber, the compressor chamber and the inlet rotatable with the fan, the compressor chamber leading toward a combustor which generates a high-energy gas stream to drive the turbine, the axial compressor rotor compressing core airflow leading to the inlet, the plurality of compressor blades including a final stage of compressor blades immediately adjacent the inlet with no intervening compressor vanes between the final state of compressor blades and the inlet.
12. The turbine engine of claim 8 wherein the planetary gearset increases a rate of rotation of the axial compressor rotor above a rate of rotation of the fan.
13. The turbine engine of claim 1 , wherein the gear is aft of the fan and the turbine.
14. The turbine engine of claim 1 , further comprising a combustor radially outward of the fan blades, the combustor configured to provide high energy gas stream to the plurality of turbine blades.
15. The turbine engine of claim 14 , wherein a core airflow passage moves air flow through the fan blades into the combustor.