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A gas turbine engine includes a fan, a compressor section fluidly connected to the fan, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor, and a buffer system. The buffer system includes a heat exchanger having a first inlet, a first outlet

A gas turbine engine includes a fan, a compressor section fluidly connected to the fan, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor, and a buffer system. The buffer system includes a heat exchanger having a first inlet, a first outlet, a second inlet, and a second outlet. The first outlet is configured to provide a cooled pressurized fluid. The buffer system includes first and second air sources that are selectively fluidly coupled to the first inlet, and a third air source that are fluidly coupled to the second inlet. Multiple fluid-supplied areas are located remotely from one another and are fluidly coupled to the first outlet. The multiple fluid-supplied areas include a bearing compartment. A method and a buffer system are also disclosed.

대표청구항 ▼

1. A gas turbine engine comprising: a fan;a compressor section fluidly connected to the fan, the compressor section including a first compressor and a second compressor each downstream of the fan;a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combu

1. A gas turbine engine comprising: a fan;a compressor section fluidly connected to the fan, the compressor section including a first compressor and a second compressor each downstream of the fan;a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combustor; anda buffer system comprising: a heat exchanger having a first inlet, a first outlet, a second inlet, and a second outlet, the first outlet configured to provide a cooled pressurized fluid;first and second air sources that are selectively fluidly coupled to the first inlet;a third air source fluidly coupled to the second inlet, the third air source being provided by the compressor section; andmultiple fluid-supplied areas located remotely from one another and fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment. 2. The gas turbine engine according to claim 1, wherein the second air source being provided by the second compressor, and the third air source being provided by the first compressor. 3. The gas turbine engine according to claim 2, wherein the first, second and third air sources are different than one another. 4. The gas turbine engine according to claim 3, wherein the first air source is configured to provide air at a first pressure and temperature state, and the second air source is configured to provide air at a higher pressure and temperature state than the first air source. 5. The gas turbine engine according to claim 4, wherein a valve is fluidly coupled to at least one of the first and second air sources, the valve configured to regulate fluid flow from at least one of the one first and second air sources to the heat exchanger. 6. The gas turbine engine according to claim 5, wherein a mid-stage is provided fluidly between the first and second compressors, the first air source being provided by the mid-stage. 7. The gas turbine engine according to claim 6, wherein the second compressor includes a rotor, and the multiple fluid-supplied areas include the rotor. 8. The gas turbine engine according to claim 1, wherein the turbine section comprises a first turbine including a shaft, and the multiple fluid-supplied areas including the shaft. 9. The gas turbine engine according to claim 8, wherein a pressure ratio across the fan is less than 1.45. 10. The gas turbine engine according to claim 9, wherein the first inlet is fluidly connected to the first outlet, and the second inlet is fluidly connected to the second outlet. 11. The gas turbine engine according to claim 8, wherein the multiple fluid-supplied areas include a component of the gas turbine engine. 12. The gas turbine engine according to claim 11, wherein the component is one of a vane, a blade and a clearance control device. 13. The gas turbine engine according to claim 12, comprising a bypass flow path arranged between core and fan nacelles, the second outlet fluidly coupled to the bypass flow path. 14. The gas turbine engine according to claim 4, wherein a mid-stage is provided fluidly between an exit of the first compressor and an entrance of the second compressor, the first air source being provided by the mid-stage. 15. The gas turbine engine according to claim 4, wherein the first air source being provided by the second compressor. 16. The gas turbine engine according to claim 15, comprising a bypass flow path arranged between core and fan nacelles, and the fan being configured to deliver a portion of air into the compressor section, and a portion of air into the bypass flow path. 17. The gas turbine engine according to claim 16, wherein the turbine section comprises a first turbine including a shaft connected to the fan through a geared reduction to drive the fan at a relatively lower speed than the first turbine. 18. The gas turbine engine according to claim 17, wherein a valve is fluidly coupled to each of the first and second air sources, the valve configured to regulate fluid flow from each of the first and second air sources to the heat exchanger. 19. The gas turbine engine according to claim 18, wherein the second compressor includes a rotor, and the multiple fluid-supplied areas include the rotor. 20. The gas turbine engine according to claim 19, wherein the multiple fluid-supplied areas includes the shaft. 21. A buffer system for a gas turbine engine comprising: a heat exchanger configured for securing to a static structure, the heat exchanger having a first inlet and outlet and a second inlet and outlet;first and second air sources selectively fluidly coupled to the first inlet; anda third air source fluidly coupled to the second inlet and being provided by a first compressor downstream of a fan;wherein the first outlet is configured to provide a cooled pressurized fluid to multiple fluid-supplied areas fluidly coupled to the first outlet, the multiple fluid-supplied areas being located remotely from one another and including a bearing compartment. 22. The buffer system according to claim 21, wherein the first air source is configured to provide air at a low pressure and temperature state, and the second air source is configured to provide air at a higher pressure and temperature state than the first air source. 23. The buffer system according to claim 21, wherein the second air source is provided by a second compressor. 24. The buffer system according to claim 21, comprising a valve configured for securing to the static structure, the valve being fluidly coupled to at least one of the first and second air sources, and the valve being configured to regulate fluid flow from the first and second air sources to the heat exchanger. 25. The buffer system according to claim 21, wherein the first inlet is fluidly connected to the first outlet, and the second inlet is fluidly connected to the second outlet. 26. The buffer system according to claim 22, wherein the second air source is provided by a second compressor, the second compressor being downstream of the first compressor and the fan. 27. The buffer system according to claim 26, wherein a mid-stage is provided fluidly between an exit of the first compressor and an entrance of the second compressor, the first air source being provided by the mid-stage.