Integrated thermal management system and environmental control system for a gas turbine engine

• US 8,978,351 B2
• Filed: 10/21/2011
• Issued: 03/17/2015
• Est. Priority Date: 10/21/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Suciu, Gabriel L., Penda, Allan R., Merry, Brian D., Glahn, Jorn A., Dye, Christoper M., Snape, Nathan
• Primary Examiner(s): Rodriguez, William H
• Application Number:
  US13/278,260
• Publication Number:
  US 20130097992A1
• Time in Patent Office: 1,243 Days
• Field of Search: 608/02, 60/390.8, 602/261, 602/62, 607/92, 60/391.62, 60/391.63, 607/83, 602/68, 607/79, 607/73, 184/4, 184/6.11, 184/6.12, 184/27.2, 244/58, 477/30, 477/31
• US Class Current: 60/39.08
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/08 Heating air supply before combustion, e.g. by exhaust gases
• CPC Class Codes: F02C 7/14 of fluids in the plant , e.g. lubricant or fuel F02C7/185 takes precedence
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02K 3/04 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
• CPC Class Codes: F05D 2260/213 by the provision of a heat exchanger within the cooling circuit
• CPC Class Codes: F05D 2260/606 Bypassing the fluid
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

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.

Claims

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.