Gas turbine engine lubrication system

Patent metadata

Field	Value
Publication number	US-9915203-B2
Application number	US-201414207949-A
Country	US
Kind code	B2
Filing date	Mar 13, 2014
Priority date	Mar 15, 2013
Publication date	Mar 13, 2018
Grant date	Mar 13, 2018

Abstract

A lubrication system for a gas turbine engine is disclosed. The lubrication system is configured to provide pressurized air and lubricant to a bearing sump of the gas turbine engine to cool and lubricate a bearing included in the bearing sump.

First claim

What is claimed is:

1. A gas turbine engine comprising
an engine core including an inlet, a compressor, a turbine, and an exhaust,
a bearing sump arranged in the engine core and operating at an operational range of about 600 degrees Fahrenheit to about 1,000 degrees Fahrenheit, and
a lubrication system configured to provide a tertiary-butyl phenyl phosphate (TBPP) lubricant to the bearing sump as a vapor, wherein the lubrication system includes an air system coupled to the bearing sump to provide air having a first temperature in a vaporization range to the bearing sump and the vapor is entrained in the air and wherein the air system includes a fuel-to-air heat exchanger configured to provide source air having a second temperature during startup and an air-to-air heat exchanger is configured to receive the source air from the fuel-to-air heat exchanger, the air-to-air heat exchanger is coupled to the exhaust to receive exhaust gas having a third temperature and configured to transfer heat from the exhaust gas to the source air to cause the source air to have the first temperature in the vaporization range, and the third temperature is greater than the second temperature.

2. The gas turbine engine of claim 1 , wherein the lubrication system includes a lubrication reservoir configured to store the TBPP lubricant as a liquid.

3. The gas turbine engine of claim 2 , wherein the lubrication system further includes a mister coupled to the lubrication reservoir to deliver the TBPP lubricant as the liquid into the bearing air being delivered to the bearing sump and the bearing air causes the TBPP lubricant to change from the liquid to the vapor before the bearing air interacts with the bearing sump.

4. The gas turbine engine of claim 2 , wherein the lubrication reservoir is located outside the engine core.

5. The gas turbine engine of claim 4 , wherein the lubrication reservoir includes an exhaust-to-lubricant heat exchanger that is configured to transfer heat from exhaust gas provided by the exhaust to the TBPP lubricant to cause the TBPP lubricant to have a temperature in a liquid range when the gas turbine engine is in a start-up mode of operation.

6. The gas turbine engine of claim 5 , wherein exhaust gas is blocked from flowing to the exhaust-to-lubricant heat exchanger when the gas turbine engine is in a steady-state mode of operation.

7. The gas turbine engine of claim 6 , wherein the lubrication reservoir further includes a layer of insulation coupled to an exterior surface of the lubrication reservoir and configured to control transfer of heat from outside air to the TBPP lubricant.

8. The gas turbine engine of claim 1 , wherein the source air has a fourth temperature greater than the second temperature when the gas turbine engine is in a steady-state mode of operation and exhaust gas is blocked from flowing to the air-to-air heat exchanger when the gas turbine engine is in the steady-state mode of operation and inlet air having a fifth temperature is provided to the air-to-air heat exchanger to cause heat to be transferred from the source air so that the bearing sump remains in the operational range when the gas turbine engine is in the steady-state mode of operation and the fifth temperature is less than the fourth temperature.

9. The gas turbine engine of claim 1 , wherein the lubrication system includes a lubrication reservoir and the lubrication reservoir includes an exhaust-to-lubricant heat exchanger that is configured to transfer heat from exhaust gas having the third temperature to the TBPP lubricant to cause the TBPP lubricant to have a temperature in a liquid range when the gas turbine engine is in a start-up mode of operation.

10. The gas turbine engine of claim 9 , wherein exhaust gas is blocked from flowing to the exhaust-to-lubricant heat exchanger when the gas turbine engine is in a steady-state mode of operation.

11. The gas turbine engine of claim 10 , wherein the lubrication reservoir further includes a layer of insulation coupled to an exterior surface of the lubrication reservoir and configured to control transfer of heat from the outside air to the TBPP lubricant and the outside air has a temperature above the liquid range.

12. The gas turbine engine of claim 1 , wherein the bearing sump includes a bearing including a steel race, ceramic rolling elements, a carbon-composite cage, and an initial dry-film solid coating applied to the steel race.

13. The gas turbine engine of claim 12 , wherein the initial dry-film solid coating is worn away from the steel race during a start-up mode of operation of the gas turbine engine to cause the steel race to be exposed to the vapor.

14. The gas turbine engine of claim 13 , wherein the vapor reacts with the steel race to form a solid lubricious layer on an outer surface of the steel race during a steady-state mode of operation.

15. A gas turbine engine comprising
an engine core including an inlet, a compressor, a turbine, and an exhaust,
a bearing sump located in the engine core and operating at an operational range of about 600 degrees Fahrenheit to about 1,000 degrees Fahrenheit, and
a lubrication system including a lubrication reservoir located outside the engine core and configured to provide a tertiary-butyl phenyl phosphate (TBPP) lubricant as a liquid lubricant to a stream of air having a temperature in a range of about 600 degrees Fahrenheit to about 800 degrees Fahrenheit to cause the TBPP lubricant to change to a vapor lubricant and be delivered to the bearing sump, wherein the lubrication system includes an air system coupled to the bearing sump to provide the stream of air having the first temperature to the bearing sump and the vapor lubricant is entrained in the stream of air and wherein the air system includes a fuel-to-air heat exchanger configured to provide the stream of air having a second temperature during startup and an air-to-air heat exchanger is configured to receive the stream of air from the fuel-to-air heat exchanger, the air-to-air heat exchanger is coupled to the exhaust to receive exhaust gas having a third temperature and configured to transfer heat from the exhaust gas to the stream of air to cause the stream of air to have the first temperature in the vaporization range, and the third temperature is greater than the second temperature.

16. The gas turbine engine of claim 15 , wherein the bearing sump includes a front seal, a first rear seal spaced apart from the front seal to locate a bearing between the front seal and the first rear seal, a second rear seal located in spaced-apart relation to the first rear seal to locate the first rear seal between the bearing and the second rear seal, and a vent formed in the bearing sump and arranged to open into the bearing sump between the first and the second rear seals.

17. The gas turbine engine of claim 16 , wherein the front seal, the first rear seal, and the second rear seal are all labyrinth seals and are configured to move the stream of air and the vapor lubricant in only one direction from the front seal towards and through the vent.

Assignees

• Rolls Royce Corp

Inventors

• Lighty Kerry J
• Junod Larry A

Classifications

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F16N7/385

  Central lubrication systems · CPC title

• F02C7/06 Primary

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F01D25/18

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title