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An assembly and method for providing buffer air and/or ventilation air within a gas turbine engine, the assembly includes an accessory gearbox and a centrifugal compressor. The accessory gearbox is connected to a driven shaft of the gas turbine engine. The centrifugal compressor is driven by the acc

An assembly and method for providing buffer air and/or ventilation air within a gas turbine engine, the assembly includes an accessory gearbox and a centrifugal compressor. The accessory gearbox is connected to a driven shaft of the gas turbine engine. The centrifugal compressor is driven by the accessory gearbox during operation of the gas turbine engine to receive and compress a bleed air to produce the buffer air and/or the ventilation air. The buffer air and/or the ventilation air is communicated within the gas turbine engine.

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1. An assembly for providing buffer air and/or ventilation air within a gas turbine engine, comprising: an accessory gearbox connected to a driven shaft of the gas turbine engine; anda centrifugal compressor driven by the accessory gearbox during operation of the gas turbine engine for receiving ble

1. An assembly for providing buffer air and/or ventilation air within a gas turbine engine, comprising: an accessory gearbox connected to a driven shaft of the gas turbine engine; anda centrifugal compressor driven by the accessory gearbox during operation of the gas turbine engine for receiving bleed air and compressing the bleed air to produce the buffer air and/or the ventilation air that is communicated within the gas turbine engine radially inward of a core flow path to at least one of a bearing compartment or driven shaft, wherein the centrifugal compressor is located radially outward of the core flow path of the gas turbine engine. 2. The assembly of claim 1, wherein the buffer air is communicated to the bearing compartment. 3. The assembly of claim 1, wherein the ventilation air is communicated to the shaft. 4. The assembly of claim 1, wherein the bleed air comprises air from a low pressure compressor section of the gas turbine engine. 5. The assembly of claim 1, wherein the bleed air comprises bypass air from a fan section of the gas turbine engine. 6. The assembly of claim 1, wherein the centrifugal compressor is disposed within a core compartment of the gas turbine engine. 7. A gas turbine engine, comprising: a shaft, a fan section, a low pressure compressor section, and at least one bearing compartment;an accessory gearbox driven by the shaft and adapted to mechanically drive one or more engine accessories; anda centrifugal compressor driven by the accessory gearbox and configured to compress air from the fan section and/or the low pressure compressor section, wherein the compressed air is communicated from the centrifugal compressor to the shaft and/or the at least one bearing compartment radially inward of a core flow path, wherein the centrifugal compressor is located radially outward of the low pressure compressor section. 8. The gas turbine engine of claim 7, wherein the gas turbine engine comprises a high bypass turbofan. 9. The gas turbine engine of claim 8, wherein the high bypass turbofan has a low pressure spool that drives the fan section through a reduction gear box. 10. The gas turbine engine of claim 7, wherein the compressed air comprises ventilation air that is directed to the shaft. 11. The gas turbine engine of claim 7, wherein the compressed air comprises buffer air that is directed to the at least one bearing compartment. 12. The gas turbine engine of claim 7, wherein the at least one bearing compartment comprises three or more bearing compartments. 13. The gas turbine engine of claim 7, wherein centrifugal compressor is disposed within a core compartment of the gas turbine engine. 14. A method of providing air from at least one of a low pressure compressor section and a fan section of a gas turbine engine to at least one of a bearing compartment and a shaft within the gas turbine engine, comprising: operating a centrifugal compressor coupled to an accessory gearbox driven by the gas turbine engine, wherein the centrifugal compressor is located radially outward of the low pressure compressor section;bleeding air from the at least one of the low pressure compressor section and the fan section to the centrifugal compressor;compressing the air with the centrifugal compressor; andcommunicating the air radially inward of a core flow path to the at least one of the bearing compartment and the shaft. 15. The method of claim 14, wherein the gas turbine engine comprises a high bypass turbofan. 16. The method of claim 15, wherein the high bypass turbofan has a low pressure spool that drives the fan section through a reduction gear box. 17. The method of claim 14, wherein the compressed air comprises a ventilation air that is directed to the shaft. 18. The method of claim 14, wherein the compressed air comprises a buffer air that is directed to the at least one bearing compartment. 19. The method of claim 14, wherein the centrifugal compressor is disposed within a core compartment of the gas turbine engine.