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 commun
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.
대표청구항▼
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 lubr
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; anda 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; anddirecting 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.
Stearns, Ethan K.; Glahn, Jorn A.; McKaveney, Daniel J., Gas turbine engine with geared turbofan and oil thermal management system with unique heat exchanger structure.
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