Integrated thermal system for a gas turbine engine
A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.
1. A thermal system for a gas turbine engine comprising:
a bypass flow duct configured to extract a fan bypass air flow from a bypass duct of said gas turbine engine;
a compressor flow duct configured to extract a bleed air flow from a compressor section of said gas turbine engine, wherein said compressor flow duct meets said bypass flow duct at an intersection to form an airflow duct;
a valve located within said intersection, said valve movable between a first position and a second position, said first position operable to selectively communicate said fan bypass air flow from said bypass flow duct and block said compressor flow duct, said second position operable to selectively communicate said bleed air flow from said compressor flow duct and block said bypass flow duct, wherein said valve communicates at least one of said fan bypass air flow and said bleed air flow to said airflow duct; and
a pump downstream of said valve in said airflow duct.
2. The thermal system as recited in claim 1 , further comprising an Air-Air PreCooler downstream of said pump.
3. The thermal system as recited in claim 2 , further comprising an Air-Oil Cooler downstream of said pump.
4. The thermal system as recited in claim 3 , wherein said Air-Air PreCooler is immediately downstream and adjacent to said Air-Oil Cooler.
5. The thermal system as recited in claim 4 , wherein the pump is downstream of a fan section in fluid communication with said Air-Oil Cooler and a fan bypass flow path.
6. The thermal system as recited in claim 5 , wherein said 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.
7. The thermal system as recited in claim 3 , wherein an airflow through said Air-Oil Cooler is transverse to an airflow through said Air-Air PreCooler.
8. The thermal system as recited in claim 3 , further comprising a second pump in fluid communication with said Air-Air PreCooler.
9. The thermal system as recited in claim 8 , wherein said second pump is operable to provide an approximately 4:1 pressure ratio at ground idle condition to said Air-Air PreCooler.
10. The thermal system as recited in claim 3 , wherein said Air-Air PreCooler is immediately downstream of said Air-Oil Cooler within a common housing.