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A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft connects with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at the

A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft connects with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at the speed of the drive shaft. The stationary torque tube is connected with a fan case in the gas turbine engine. The gear system is connected to the second-stage fan shaft and the torque tube. The first-stage fan shaft extends from the gear system such that the first-stage fan shaft is driven at a speed reduced from that of the drive shaft.

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1. A two-stage turbofan system for use in a gas turbine engine through which inlet air travels from an upstream direction to a downstream direction, the two-stage turbofan system comprising: a second-stage fan shaft for connection with a drive shaft in the gas turbine engine such that the second-sta

1. A two-stage turbofan system for use in a gas turbine engine through which inlet air travels from an upstream direction to a downstream direction, the two-stage turbofan system comprising: a second-stage fan shaft for connection with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at a speed of the drive shaft;a stationary torque tube having a fixed upstream portion for connection with a fan case in the gas turbine engine;a gear system comprising: a ring gear connected to the second-stage fan shaft;a stationary sun gear connected to a downstream portion of the torque tube concentric with the ring gear; anda gear carrier positioned concentrically between the ring gear and the sun gear, the gear carrier having a plurality of planet gears positioned in the gear carrier to interface with the sun gear and the ring gear; anda first-stage fan shaft having a downstream portion extending from the gear carrier such that the first-stage fan shaft is driven at a speed reduced from that of the drive shaft. 2. The two-stage turbofan system of claim 1 wherein the gear system comprises an epicylic gear train. 3. The two-stage turbofan system of claim 1 and further comprising a plurality of journal pins positioned within the plurality of planet gears and connected to the carrier. 4. The two-stage turbofan system of claim 3 and further comprising: an oil manifold connected to the plurality of journal pins; andan oil feed extending through the stationary torque tube and connecting with the oil manifold. 5. The two-stage turbofan system of claim 4 wherein the plurality of journal pins include radially extending lubrication bores such that oil from the oil manifold can be centrifically driven from the oil manifold to the interface of the ring gear and the plurality of planet gears. 6. The two-stage turbofan system of claim 5 and further comprising an oil collection system for gathering oil centrifically passed through the gear system. 7. The two-stage turbofan system of claim 1 wherein: the second-stage fan shaft comprises: a downstream portion connected to the drive shaft;an upstream portion connectable to a high speed fan stage; andan intermediate portion connected to the ring gear;the downstream portion of the first-stage fan shaft extends axially from the gear carrier in an upstream direction such that an upstream portion of the first-stage fan shaft is connectable to a low speed fan stage; andthe downstream portion of the stationary torque tube extends axially from the sun gear in an upstream direction such that an upstream portion of the torque tube is connectable with an inlet guide vane. 8. The two-stage turbofan system of claim 7 wherein the intermediate portion of the second-stage fan shaft includes a radially extending bulge connected to an outer diameter of the gear system such that the radially extending bulge includes a diameter greater than that of the upstream and downstream portions of the second-stage fan shaft. 9. The two-stage turbofan system of claim 7 wherein the first-stage fan shaft is disposed radially between the stationary torque tube and the second-stage fan shaft. 10. A drive system for a two-stage turbofan gas turbine engine, the drive system comprising: a first shaft system connected to a turbine within the gas turbine engine for driving a high speed fan stage section;a static torque tube disposed coaxially with the first shaft system, the static torque tube being anchored to the gas turbine engine in a non-rotating fashion;a planetary gear system coupled between the first shaft system and the static torque tube, the planetary gear system comprising: a static sun gear positioned around the static torque tube;a gear carrier positioned concentrically around the sun gear;a plurality of planet gears positioned in the gear carrier such that the planet gears interface with the sun gear; anda ring gear positioned concentrically around the gear carrier such that the ring gear interfaces with the plurality of planet gears and the first shaft system; anda second shaft system connected to the gear carrier of the planetary gear system for driving a low speed fan stage section. 11. The drive system for a two-stage turbofan gas turbine engine of claim 10 wherein the first shaft system comprises a high speed fan shaft comprising: a first end for connecting with a turbine drive shaft;a second end for connecting with a high speed fan blade rotor; andan arched middle portion for connecting with the ring gear of the planetary gear system;wherein outer diameters of the middle portion and the second end are extended radially farther than an outer diameter of the first end. 12. The drive system for a two-stage turbofan gas turbine engine of claim 11 wherein the second shaft system comprises a low speed shaft, and wherein the static torque tube extends axially forward from the sun gear and the low speed shaft extends axially forward from the gear carrier such that the low speed shaft is disposed concentrically between the static torque tube and the high speed shaft. 13. The drive system for a two-stage turbofan gas turbine engine of claim 12 wherein the low speed shaft is connected to a low speed fan blade rotor, wherein the low speed fan blade rotor is disposed axially forward of the high speed fan blade rotor. 14. The drive system for a two-stage turbofan gas turbine engine of claim 12 wherein the first and second ends of the high speed fan shaft are supported by bearings mounted to stationary struts within the gas turbine engine, and the low speed fan shaft is supported by a bearing positioned between the high speed fan shaft and the low speed fan shaft. 15. The drive system for a two-stage turbofan gas turbine engine of claim 10 wherein the planetary gear system reduces the rotational output speed of the second shaft system to about eighty-three percent of that of the first shaft system. 16. The drive system for a two-stage turbofan gas turbine engine of claim 10 wherein a forward end of the static torque tube is connected with an inlet guide vane of the gas turbine engine. 17. A gear system for use in a two-stage turbofan engine, the gear system comprising: a static shaft for connection to a non-rotating member of the turbofan engine;a sun gear affixed to the static shaft such that it is non-rotating about the static shaft;a gear carrier positioned concentrically around the sun gear, the gear carrier comprising: a plurality of gear slots circumferentially disposed about a circumference of the gear carrier;a plurality of journal pins extending through the plurality of gear slots;a plurality of planet gears disposed about the journal pins within the gear slots such that the planet gears interface with the sun gear; anda plurality of torque slots extending through the gear carrier between the plurality of gear slots;a ring gear positioned concentrically around the gear carrier such that the ring gear interfaces with the plurality of planet gears;a first-stage drive shaft connected to the torque slots and extending axially from the gear carrier for connection to a first-stage fan;a first conical drive shaft connected to the ring gear and extending axially from the ring gear in a first direction for connection to a second-stage fan; anda second conical drive shaft connected to the ring gear and extending axially from the ring gear in a second direction for connection to an input turbine shaft. 18. The gear system of claim 17 and further comprising: a plurality of spray bars disposed between the plurality of planet gears and configured for riding in circumferential grooves within the plurality of planet gears; andan oil manifold connected to the gear carrier and configured for dispersing oil to the plurality of spray bars.