Gas turbine engine with air-oil cooler oil tank

1. An air-oil cooler oil tank system comprising:

a bypass duct;

a cooler duct comprising a cooler duct outlet;

an annular oil tank adjacent the cooler duct;

a fan airflow diverter at an end of the cooler duct and upstream of said annular oil tank;

a bleed compartment which contains said fan airflow diverter and said annular oil tank;

the cooler duct configured to receive air through the fan airflow diverter from the bypass duct and direct the received air axially along the annular oil tank through the cooler duct outlet and back into the bypass duct; and

a bleed duct comprising a bleed duct outlet, the bleed duct configured to direct bleed air through the bleed duct outlet into the bypass duct, and the bleed duct outlet adjacent to and downstream of the cooler duct outlet.

2. The system as recited in claim 1 , wherein said annular oil tank is in fluid communication with a geared architecture.

3. The system as recited in claim 1 , further comprising an array of cooling fins defined about an outer diameter of said annular oil tank, said fan airflow diverter in communication with said array of cooling fins.

4. The system as recited in claim 3 , wherein said array of cooling fins include a shroud that is flush along a fan bypass flowpath.

5. The system as recited in claim 3 , wherein said array of cooling fins include a shroud that is flush with a core nacelle.

6. The system as recited in claim 3 , wherein said array of cooling fins are downstream of a Fan Exit Guide Vane array.

7. The system as recited in claim 3 , wherein said array of cooling fins are defined about an outer periphery of said annular oil tank.

8. The system as recited in claim 1 , further comprising a shield radially inboard of said annular oil tank.

9. The system as recited in claim 1 , wherein said annular oil tank is manufactured of a multiple of arcuate segments.