A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicat
A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.
대표청구항▼
1. A gas turbine engine, comprising: a compressor section;a combustor in fluid communication with said compressor section;a turbine section in fluid communication with said combustor;a fan section configured to be driven by the turbine section via a geared architecture; anda buffer system that commu
1. A gas turbine engine, comprising: a compressor section;a combustor in fluid communication with said compressor section;a turbine section in fluid communication with said combustor;a fan section configured to be driven by the turbine section via a geared architecture; anda buffer system that communicates buffer air to a portion of the gas turbine engine, wherein the buffer system includes a first circuit including a valve configured to selectively mix, based on a power condition of the gas turbine engine, a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure, and wherein the valve is in communication with the first bleed air supply and the second bleed air supply. 2. The gas turbine engine as recited in claim 1, wherein the buffer system includes a second circuit that selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer air supply to a different portion of the gas turbine engine. 3. The gas turbine engine as recited in claim 2, wherein one of said first circuit and said second circuit includes a conditioning device. 4. The gas turbine engine as recited in claim 2, wherein at least one of said first circuit and said second circuit includes at least one of an ejector and a valve. 5. The gas turbine engine as recited in claim 2, wherein the gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than about six (6). 6. The gas turbine engine as recited in claim 5, wherein the bypass ratio is greater than about ten (10). 7. The gas turbine engine as recited in claim 6, wherein the gas turbine engine includes a Fan Pressure Ratio of less than about 1.45. 8. The gas turbine engine as recited in claim 7, wherein the turbine section includes a fan drive turbine configured to drive the fan section through the geared architecture and the fan drive turbine section is configured to rotate at a first speed and the fan section is configured to rotate at a second speed less than the first speed. 9. The gas turbine engine as recited in claim 8, wherein the fan drive turbine has a pressure ratio that is greater than about five (5). 10. The gas turbine engine as recited in claim 9, wherein fan drive turbine is arranged on a first spool supported for rotation about an engine axis by at least one bearing structure arranged in a bearing compartment. 11. The gas turbine engine as recited in claim 10, wherein at least one of the first and second circuits supplies buffer supply air to the at least one bearing compartment. 12. The gas turbine engine as recited in claim 11, wherein the at least one bearing compartment is in the turbine section. 13. The gas turbine engine as recited in claim 11, wherein the at least one bearing compartment comprises a first bearing compartment aft of the geared architecture and a second bearing compartment forward of the geared architecture. 14. The gas turbine engine as recited in claim 10, wherein the geared architecture includes an epicyclic gear train. 15. The gas turbine engine as recited in claim 14, wherein the epicyclic gear train is a planetary gear system. 16. The gas turbine engine as recited in claim 14, wherein the epicyclic gear train has a gear reduction ratio of greater than about 2.3. 17. The gas turbine engine as recited in claim 16, wherein the epicyclic gear train has a gear reduction ratio of greater than about 2.5. 18. The gas turbine engine as recited in claim 14, wherein the compressor section comprises a first compressor and a second compressor and the turbine section comprises the fan drive turbine and a second turbine, wherein the second compressor and the second turbine are arranged on a second spool, the second spool including at least one bearing system arranged in a bearing compartment, and at least one of the first and second circuits supplies buffer supply air to the at least one bearing compartment. 19. The engine as recited in claim 18, wherein the turbine section includes the fan drive turbine, the second turbine and a third turbine, wherein the second turbine and the third turbine are configured to drive the first compressor and the second compressor. 20. The gas turbine engine as recited in claim 18, wherein the second spool rotates faster than the first spool. 21. A method of designing a gas turbine engine comprising: defining a compressor section;defining a combustor in fluid communication with the compressor section;defining a turbine section in fluid communication with said combustor;defining a fan section configured to be driven by a turbine section via a geared architecture; andconfiguring a buffer system for communicating buffer air to a portion of the gas turbine engine, wherein the buffer system is defined to include a first circuit for selectively mixing via a single valve, based on a power condition of the gas turbine engine, a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure. 22. The method of designing as recited in claim 21, including defining the buffer system to include a second circuit that selects between a third bleed air supply and a fourth bleed air supply for communicating a second buffer air supply to a different portion of the gas turbine engine. 23. The method as recited in claim 22, including defining one of said first circuit and said second circuit to include a conditioning device. 24. The method as recited in claim 23, including configuring at least one of said first circuit and said second circuit to include at least one of an ejector and a valve. 25. The method as recited in claim 24, including defining the turbine section to include a fan drive turbine configured to drive the fan section through the geared architecture and configuring the fan drive turbine section to rotate at a first speed and the fan section to rotate at a second speed less than the first speed. 26. The method as recited in claim 25, including configuring the fan drive turbine to include a pressure ratio greater than about five (5). 27. The method as recited in claim 26, including configuring the fan drive turbine on a first spool supported for rotation about an engine axis by at least one bearing structure arranged in a bearing compartment. 28. The method as recited in claim 27, including configuring at least one of the first and second circuits to supply buffer supply air to the at least one bearing compartment. 29. The method as recited in claim 28, wherein the at least one bearing compartment is in the turbine section. 30. The method as recited in claim 28, wherein the at least one bearing compartment comprises a first bearing compartment aft of the geared architecture and a second bearing compartment forward of the geared architecture. 31. The gas turbine engine as recited in claim 1, wherein when the gas turbine engine is in a high power state, the first buffer supply air comprises more of the first bleed air supply than the second bleed air supply. 32. The gas turbine engine as recited in claim 1, wherein when the gas turbine engine is in a low power state, the first buffer supply air comprises more of the second bleed air supply than the first bleed air supply.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (7)
Mortzheim, Jason Paul; Zhou, Ming; Marks, Paul Thomas, Apparatus and methods for controlling flow in turbomachinery.
Anderson, Morris G.; Banta, Paul W.; Brackin, James W.; Romano, Robert; Zmora, David W., Variable geometry ejector for a bleed air system using integral ejector exit pressure feedback.
Wolfe, Christopher E.; Beadie, Douglas F.; Whaling, Kenneth N.; Ball, David W.; McGovern, Kevin T.; Eluripati, Ravi Praveen; Samudrala, Omprakash, Variable motive nozzle ejector for use with turbine engines.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.