Thermal management system for a gas turbine engine

1. A thermal management system for a gas turbine engine comprising:

a forward cover having a filter portion along an axis of rotation of a gas turbine engine;

a rotor shaft along said axis of rotation;

a forward rotor shaft bearing which rotationally supports said rotor shaft;

an aft rotor shaft bearing which rotationally supports said rotor shaft, said forward rotor shaft bearing and said aft rotor shaft bearing in communication with a cooling airflow from said filter portion; and

a forward housing defined about said axis of rotation, said forward housing defining a lubrication passage directed toward said forward rotor bearing, said forward cover mounted to said forward housing.

2. The thermal management system as recited in claim 1 , wherein said forward cover is forward of a rotor shaft defined along said axis of rotation.

3. A thermal management system for a gas turbine engine comprising:

a forward cover having a filter portion along an axis of rotation of a gas turbine engine;

a rotor shaft along said axis of rotation;

a forward rotor shaft bearing which rotationally supports said rotor shaft;

an aft rotor shaft bearing which rotationally supports said rotor shaft, said forward rotor shaft bearing and said aft rotor shaft bearing in communication with a cooling airflow from said filter portion; and

a permanent magnet generator (PMG) mounted to said rotor shaft, said PMG mounted between said forward rotor shaft bearing and said aft rotor shaft bearing.

4. The thermal management system as recited in claim 1 , wherein said forward cover is mounted to a forward housing defined about said axis of rotation, said forward cover located forward of a rotor shaft which rotates about said axis of rotation.

5. A gas turbine engine comprising:

a rotor shaft defined along an axis of rotation;

a compressor wheel mounted to said rotor shaft;

at least one rotor shaft bearing which supports said rotor shaft;

a forward cover having a filter portion adjacent said rotor shaft;

a forward housing which defines a forward housing inner support and an air intake to communicate airflow toward said compressor wheel, said forward cover mounted to said forward housing such that cooling airflow through said filter portion is communicated through said forward housing inner support toward said at least one rotor shaft bearing, said forward housing defines at least one lubricant passage directed toward said at least one rotor shaft bearing such that said lubricant passage is in communication with said cooling airflow.

6. The gas turbine engine as recited in claim 5 , wherein said at least one rotor shaft bearing includes a forward rotor shaft bearing and an aft rotor shaft bearing mounted to said rotor shaft.

7. The gas turbine engine as recited in claim 5 , wherein said forward housing inner support retains said at least one bearing.

8. The gas turbine engine as recited in claim 5 , wherein said forward housing defines at least one lubricant passage directed toward said at least one rotor bearing, said lubricant passage in communication with said cooling airflow.

9. The gas turbine engine as recited in claim 5 , further comprising:

a fastener threaded to a threaded end segment of said rotor shaft, said filter portion forward of said threaded end segment.

10. The gas turbine engine as recited in claim 9 , wherein said forward cover at least partially receives said fastener therein.

11. The gas turbine engine as recited in claim 5 , wherein said gas turbine engine produces at a maximum, less than 150 pounds of thrust.

12. A method of thermal management for a gas turbine engine comprising the steps of:

(1) communicating a cooling airflow through a filter portion along an axis of rotation of a rotor shaft having a compressor wheel, the cooling airflow in communication with at least one rotor bearing which supports the rotor shaft;

(2) merging the cooling airflow into a primary airflow path downstream of the at least one bearing, the primary airflow path in communication with the compressor wheel; and

(3) communicating the cooling airflow past a lubricant passage to at least partially atomize a lubricant therefrom such that atomized lubricant is received onto the at least one bearing.

13. A method as recited in claim 12 , further comprising the step of:

(4) communicating a primary airflow along the primary airflow path from an intake defined at least partially about the periphery of a forward cover which supports the filter portion.

14. A method as recited in claim 12 , further comprising the step of:

(4) communicating the cooling airflow through a forward housing inner support; and

(5) supporting the at least one bearing within the forward housing inner support.

15. A gas turbine engine comprising:

a rotor shaft defined along an axis of rotation;

a compressor wheel mounted to said rotor shaft;

a forward housing which defines a forward housing inner support and an air intake to communicate a primary airflow toward said compressor wheel; and

a forward cover having a filter portion forward of said rotor shaft and radially inward of said air intake, said forward cover mounted to said forward housing inner support such that a cooling airflow is communicated through said filter portion and into said forward housing inner support;

a forward rotor shaft bearing forward of said compressor wheel to rotationally support said rotor shaft;

an aft rotor shaft bearing forward of said compressor wheel and aft of said forward rotor shaft bearing to rotationally support said rotor shaft, said forward rotor shaft bearing and said aft rotor shaft bearing in communication with the cooling airflow, the cooling airflow communicated to merge with the primary airflow from the air intake upstream of said compressor wheel to provide a combined airflow toward the compressor wheel.