Gas turbine engine with compressor inlet guide vane positioned for starting

1. A gas turbine engine comprising:

a compressor section;

a low spool;

a high spool;

a fan section including a fan and an outer housing surrounding said fan to establish a bypass duct;

said fan for delivering air into said compressor section, and said compressor section compressing the air and for delivering the air into a combustion section;

said compressor section including a variable inlet guide vane which is movable between distinct angles to control airflow approaching said compressor section;

a control programmed to position said variable inlet guide vane at startup of the gas turbine engine to direct the airflow across said compressor section; and

a starter coupled to the low spool and the high spool such that the starter drives the low spool and the high spool in combination with windmilling in response to an aircraft associated with the gas turbine engine being in the air at an air speed that is below a speed threshold;

said fan also for delivering bypass air into said bypass duct, said bypass duct positioned outwardly of a core engine including said compressor section; and

wherein the position of said variable inlet guide vane is configured to direct the airflow across said compressor section while the aircraft associated with the gas turbine engine is in the air, and to increase a windmilling speed of said compressor section and turbine rotors.

2. The gas turbine engine as set forth in claim 1 , comprising an actuator to change the angle of the guide variable inlet vane, said actuator being responsive to said control.

3. The gas turbine engine as set forth in claim 2 , wherein said compressor section includes a first compressor and a second compressor, and the first compressor is upstream of the second compressor.

4. The gas turbine engine as set forth in claim 3 , comprising a geared architecture configured to drive said fan at a lower speed than said low spool, said geared architecture being driven by said low spool.

5. The gas turbine engine as set forth in claim 1 , wherein said compressor section includes a first compressor and a second compressor.

6. The gas turbine engine as set forth in claim 5 , wherein variable inlet guide said vane is positioned forwardly of an upstream most rotor in the first compressor.

7. The gas turbine engine as set forth in claim 6 , wherein said fan is driven with said first compressor by said low spool, and there being a gear reduction between said fan and said low spool.

8. The gas turbine engine as set forth in claim 7 , wherein said control includes stored desired positions for said variable inlet guide vane to provide increased airflow into the compressor section at startup at various conditions.

9. The gas turbine engine as set forth in claim 8 , wherein said various conditions include the altitude of the aircraft carrying the gas turbine engine, and the air speed of the aircraft.

10. The gas turbine engine as set forth in claim 9 , wherein the various conditions also include a speed of said low spool, said low spool rotating with said first compressor when startup is occurring.

11. The gas turbine engine as set forth in claim 10 , wherein said bypass duct having a variable area nozzle, and the position of the variable area nozzle also being controlled at startup to provide airflow through said bypass duct and across said fan to increase the windmilling speed.

12. The gas turbine engine as set forth in claim 11 , wherein the control is programmed to cause the windmilling speed to increase at startup of the engine by adjusting the position of said variable inlet guide vane such that the airflow across said compressor section is increased.

13. The gas turbine engine as set forth in claim 12 , wherein the control is programmed to cause said variable area nozzle to move to a fully open position at startup of the gas turbine engine such that the windmilling speed is increased.