Integrated thermal management system and environmental control system for a gas turbine engine
A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler.
1. A gas turbine engine comprising:
a spool;
a first pump driven by said spool;
an air-oil cooler downstream of said first pump;
a second pump driven by said spool, wherein said first pump and said second pump are driven by said spool through a constant speed transmission; and
an air-air precooler downstream of said second pump, said air-air precooler downstream of said air-oil cooler.
2. The gas turbine engine as recited in claim 1 , wherein said spool drives a fan through a geared architecture.
3. The gas turbine engine as recited in claim 1 , wherein said spool operates at speed excursions of up to 80% between a first condition and a second condition.
4. The gas turbine engine as recited in claim 1 , wherein said first pump is an axial pump stage.
5. The gas turbine engine as recited in claim 1 , wherein said second pump is a centrifugal pump stage.
6. The gas turbine engine as recited in claim 1 , wherein said first pump is an axial pump stage and said second pump is a centrifugal pump stage.
7. The gas turbine engine as recited in claim 1 , wherein said first pump and said second pump are in fluid communication with an annular fan bypass.
8. The gas turbine engine as recited in claim 7 , wherein said air-air precooler exhausts into said annular fan bypass to provide thrust recovery.
9. A gas turbine engine comprising:
a spool;
a constant speed transmission driven by said spool;
a first pump driven by said constant speed transmission;
an air-oil cooler downstream of said first pump; and
an air-air precooler downstream of said an air-oil cooler.
10. The gas turbine engine as recited in claim 9 , further comprising a second pump driven by said constant speed transmission, said air-air precooler downstream of said second pump.
11. The gas turbine engine as recited in claim 10 , wherein said spool is a low spool that drives a fan through a geared architecture.
12. The gas turbine engine as recited in claim 11 , wherein said constant speed transmission is driven by said low spool through a towershaft.
13. The gas turbine engine as recited in claim 9 , wherein said constant speed transmission provides a 5:1 continuously variable gear ratio capability.
14. The gas turbine engine as recited in claim 9 , wherein said spool operates at speed excursions of up to 80% between a first condition and a second condition.
15. A gas turbine engine comprising:
a low spool along an engine axis;
a high spool along said engine axis;
a first pump driven by said low spool;
a second pump driven by said low spool, wherein said first pump and said second pump are driven by said low spool through a constant speed transmission;
an air-oil cooler downstream of said first pump;
an accessory gearbox driven by said high spool; and
an air-air precooler downstream of said second pump, said air-air precooler downstream of said air-oil cooler.
16. The gas turbine engine as recited in claim 15 , wherein said low spool operates at speed excursions of up to 80% between a first condition and a second condition and said high spool operates at speed excursions of up to 30% between said first condition and said second condition.