Gas turbine engine lubrication system

• US 10,145,302 B2
• Filed: 02/26/2014
• Issued: 12/04/2018
• Est. Priority Date: 03/04/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Roberge, Gary D.
• Primary Examiner(s): Laurenzi, Mark
• Assistant Examiner(s): FRANCE, MICKEY H
• Application Number:
  US14/768,232
• Publication Number:
  US 20150361888A1
• Time in Patent Office: 1,742 Days
• Field of Search: 415 1, 415110, 415111
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F05D 2260/98 Lubrication

Abstract

A gas turbine engine according to an exemplary aspect of the present disclosure includes, a shaft including at least one bearing, a speed change device in communication with the shaft, a first lubrication system in communication with the at least one bearing and a second lubrication system in communication with the speed change device.

Claims

1. A gas turbine engine comprising:

a shaft including at least one bearing;

a speed change device in communication with the shaft;

a first lubrication system in communication with the at least one bearing;

a second lubrication system in communication with the speed change device, wherein the first lubrication system is fluidly isolated from the second lubrication system; and

a third lubrication system in communication with a second speed change device and the third lubrication system is fluidly isolated from the first lubrication system and the second lubrication system.

2. The gas turbine engine of claim 1, wherein the first lubrication system includes a first fluid condition sensor configured to monitor fluid entering the at least one bearing.

3. The gas turbine engine of claim 2, wherein the first lubrication system includes a pump and at least one heat exchanger.

4. The gas turbine engine of claim 2, wherein the first lubrication system includes a second fluid condition sensor located downstream of the at least one bearing configured to monitor fluid exiting the at least one bearing.

5. The gas turbine engine of claim 4, wherein the first fluid condition sensor and the second fluid condition sensor are configured to monitor at least one of flow rate, pressure, temperature, lubricant condition, and metal or other contaminant content.

6. The gas turbine engine of claim 1, wherein the second lubrication system includes a first fluid condition sensor configured to monitor fluid entering the speed change device.

7. The gas turbine engine of claim 6, wherein the second lubrication system includes a pump and at least one heat exchanger.

8. The gas turbine engine of claim 6, wherein the second lubrication system includes a second fluid condition sensor located downstream of the speed change device configured to monitor fluid exiting the speed change device.

9. The gas turbine engine of claim 8, wherein the first fluid condition sensor and the second fluid condition sensor are configured to monitor at least one of flow rate, pressure, temperature, lubricant condition, and metal or other contaminant content.

10. The gas turbine engine of claim 1, wherein the second lubrication system is in fluid communication with at least one shaft bearing.

11. The gas turbine engine of claim 1, wherein the first lubrication system is in fluid communication with at least one accessory drive.

12. The gas turbine engine of claim 1, wherein the first lubrication system is in fluid communication with at least one gearbox.

13. The gas turbine engine of claim 1, wherein the speed change device is an epicyclic gear train.

14. A method of lubricating a gas turbine engine comprising the steps of:

directing a first lubricant to at least one bearing with a first lubrication system; and

directing a second lubricant to a speed change device with a second lubrication system, wherein the at least one bearing includes a plurality of shaft bearings, the first lubrication system is fluidly isolated from the second lubrication system, and the first lubricant is a different lubricant from the second lubricant.

15. The method of claim 14, including monitoring a condition of the second lubricant in the second lubrication system before the second lubricant enters the speed change device.

16. The method of claim 14, including monitoring a condition of the first lubricant in the first lubrication system before the first lubricant enters the at least one bearing.

17. The method of claim 14, wherein the first lubrication system directs the first lubricant at a first flow rate and the second lubrication system directs the second lubricant at a second flow rate, the first flow rate being greater than the second flow rate.

18. The method of claim 14, wherein the first lubrication system maintains an operating condition at a first predetermined value and the second lubrication maintains the operating characteristic at a second predetermined value different from the first predetermined value.