Gas turbine engine accessory architecture

• US 10,634,061 B2
• Filed: 02/04/2015
• Issued: 04/28/2020
• Est. Priority Date: 03/06/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Snyder, Ryan K., Heims, Eric J., Colebrook, Mark W.
• Primary Examiner(s): Kim, Craig
• Application Number:
  US15/111,572
• Publication Number:
  US 20160333791A1
• Time in Patent Office: 1,910 Days
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64D 27/10 of gas-turbine type jet aircraft B64D27/16
• CPC Class Codes: B64D 29/06 Attaching of nacelles, fairings or cowlings
• CPC Class Codes: B64D 29/08 Inspection panels for power plants
• CPC Class Codes: F01D 25/20 using lubrication pumps
• CPC Class Codes: F01D 25/265 Vertically split casings; Clamping arrangements therefor
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• 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 3/06 with front fan
• CPC Class Codes: F05D 2220/327 to drive shrouded, high solidity propeller
• CPC Class Codes: F05D 2230/72 Maintenance
• CPC Class Codes: F05D 2250/30 Arrangement of components
• CPC Class Codes: F05D 2250/411 in rotation
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine comprises a compressor, a combustor and a turbine. A housing for the gas turbine engine includes a mount member to define a vertically upper location. Sides of the engine are defined on opposed sides of the mount, with a fuel filter, a fuel pump and a fuel flow meter being positioned on a first side and an oil pump, an oil filter and an oil tank positioned on a second of the sides.

Claims

1. A gas turbine engine comprising:

a compressor, a combustor and a turbine;

a housing for said gas turbine engine, with said housing including a mount member to define a vertically upper location, and sides of the engine being defined on opposed sides of the mount, with a fuel filter, a fuel pump and a fuel flow meter being positioned on a first side and an oil pump, an oil filter and an oil tank positioned on a second of said sides; and

wherein pivoting doors are associated with each of the said first and second sides to provide access to components.

2. The gas turbine engine as set forth in claim 1, wherein an electronic engine control, a prognostic health and monitoring unit and an igniter box are all positioned on one of said first and second sides.

3. The gas turbine engine as set forth in claim 2, wherein a fuel/oil cooler is positioned at a vertically upper location.

4. The gas turbine engine as set forth in claim 2, wherein said fuel pump is positioned vertically below the fuel flow meter.

5. The gas turbine engine as set forth in claim 4, wherein said oil pump is positioned vertically below said oil tank.

6. The gas turbine engine as set forth in claim 5, wherein a main gearbox is positioned in a vertically lower location.

7. The gas turbine engine as set forth in claim 6, wherein a generator is also positioned in said vertically lower location.

8. The gas turbine engine as set forth in claim 1, wherein a fuel/oil cooler is positioned at a vertically upper location.

9. The gas turbine engine as set forth in claim 1, wherein said fuel pump is positioned vertically below the fuel flow meter.

10. The gas turbine engine as set forth in claim 1, wherein said oil pump is positioned vertically below said oil tank.

11. The gas turbine engine as set forth in claim 9, wherein a main gearbox is positioned in a vertically lower location.

12. The gas turbine engine as set forth in claim 11, wherein a generator is also positioned in said vertically lower location.

13. The gas turbine engine as set forth in claim 1, wherein a generator is positioned at a vertically lower location.