Integrated thermal system for a gas turbine engine

1. An integrated thermal system for a gas turbine engine comprising:

an Air-Air PreCooler immediately downstream and adjacent to an Air-Oil Cooler;

a first pump downstream of a fan section in fluid communication with said Air-Oil Cooler and a fan bypass flow path, wherein said first pump is operable to provide a 1.4:1 pressure ratio from said fan bypass flow path of the gas turbine engine to said Air-Oil Cooler.

2. The integrated thermal system as recited in claim 1 , wherein an airflow through said Air-Oil Cooler is transverse to an airflow through said Air-Air PreCooler.

3. The integrated thermal system as recited in claim 1 , further comprising a second pump in fluid communication with said Air-Air PreCooler.

4. The integrated thermal system as recited in claim 3 , wherein said second pump is operable to provide an approximately 4:1 pressure ratio at ground idle condition to said Air-Air PreCooler.

5. The integrated thermal system as recited in claim 1 , wherein said Air-Air PreCooler is immediately downstream of said Air-Oil Cooler within a common housing.

6. A gas turbine engine comprising:

a first pump downstream of a fan section in fluid communication with a fan bypass flow path;

a second pump;

an Air-Oil Cooler downstream of said first pump; and

an Air-Air PreCooler downstream of said second pump, said Air-Air PreCooler immediately downstream and adjacent to said Air-Oil Cooler, wherein said first pump is operable to provide a 1.4:1 pressure ratio from said fan bypass flow path of the gas turbine engine to said Air-Oil Cooler and said second pump is operable to provide an approximately 4:1 pressure ratio at ground idle condition to said Air-Air PreCooler.

7. The gas turbine engine as recited in claim 6 , wherein an airflow through said Air-Oil Cooler is transverse to an airflow through said Air-Air PreCooler.