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A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has

A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has a core case containing a core engine.

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1. A fan section of a gas turbine engine comprising: a fan case radially surrounding a fan hub;a plurality of fan exit guide vanes connected between the fan hub and the fan case at a first axial location, wherein the plurality of fan exit guide vanes includes a first set of fan exit guide vanes that

1. A fan section of a gas turbine engine comprising: a fan case radially surrounding a fan hub;a plurality of fan exit guide vanes connected between the fan hub and the fan case at a first axial location, wherein the plurality of fan exit guide vanes includes a first set of fan exit guide vanes that are rotatable between an open position and a closed position and a second set of fan exit guide vanes that are fixed in the open position, and wherein the first axial location is disposed axially upstream of a second axial location where an inlet duct of a core engine is disposed, such that a core portion of air passes through the second set of fan exit guide vanes before entering the inlet duct of the core engine; anda thrust reverser opening within the fan case, axially upstream of the plurality of fan exit guide vanes. 2. The fan section of claim 1, further comprising a plurality of blades axially upstream of the thrust reverser opening. 3. The fan section of claim 2, wherein a ratio of the plurality of fan exit guide vanes to the blades is greater than one. 4. The fan section of claim 1 further comprising a translating sleeve attached to the fan case at the thrust reverser opening. 5. The fan section of claim 1, wherein at least two of the first set of fan exit guide vanes are mechanically connected to each other to allow the at least two guide vanes to rotate together. 6. The fan section of claim 5 further comprising an actuator connected to the at least two exit guide vanes mechanically connected to each other. 7. The fan section of claim 1 further comprising a core exhaust outlet axially downstream of the thrust reverser opening. 8. A gas turbine engine comprising: a fan case radially surrounding a fan hub;a plurality of fan exit guide vanes connected between the fan hub and the fan case at a first axial location, wherein the plurality of fan exit guide vanes includes a first set of fan exit guide vanes that are rotatable between an open position and a closed position and a second set of fan exit guide vanes that are fixed in the open position;a thrust reverser opening within the fan case, axially upstream of the plurality of fan exit guide vanes; anda core case containing a core engine, the core engine having a compressor, a combustor, a turbine, and a core inlet configured to supply a core portion of air to the compressor, the combustor, and the turbine, the core inlet disposed at a second axial location axially downstream from the first axial location such that the core portion of air passes through the second set of fan exit guide vanes before entering the inlet duct of the core engine. 9. The gas turbine engine of claim 8 further comprising a plurality of blades axially upstream of the thrust reverser opening. 10. The gas turbine engine of claim 8 wherein the core case has a core axis and the fan case has a fan axis, and whereby the core axis is not parallel to the fan axis. 11. The gas turbine engine of claim 8 wherein the core engine comprises a reverse flow engine. 12. The gas turbine engine of claim 8 further comprising a translating sleeve attached to the fan case. 13. The gas turbine engine of claim 8 wherein at least two of the first set of fan exit guide vanes are mechanically connected to each other to allow the at least two guide vanes to rotate together. 14. The gas turbine engine of claim 13 further comprising an actuator connected to the at least two exit guide vanes mechanically connected to each other. 15. The gas turbine engine of claim 8 wherein the core inlet is located adjacent the second set of fan exit guide vanes. 16. The gas turbine engine of claim 8 further comprising a core exhaust outlet axially downstream of the thrust reverser opening. 17. A reverse flow core gas turbine engine comprising: a fan section defined about a fan axis, the fan section including:a fan case;a fan hub;a plurality of fan exit guide vanes attached between the fan case and the fan hub at a first axial location; anda thrust reverser cascade within said fan case axially upstream of the plurality of fan exit guide vanes;wherein the plurality of fan exit guide vanes includes a first set of fan exit guide vanes that are rotatable between an open position and a closed position and a second set of fan exit guide vanes that are fixed in the open position; anda core section defined about a core axis, the core section attached to the fan section, a core inlet duct for providing air to the core section, the core inlet duct disposed at a second axial location axially downstream from the first axial location such that a core portion of air passes through the second set of fan exit guide vanes before entering the inlet duct of the core engine. 18. The reverse flow core gas turbine engine of claim 17 wherein the core axis and the fan axis are angled with respect to one another.