Buffer air assembly for an aircraft engine

An engine for an aircraft, the engine comprising:

• a low-pressure compressor;
• a high-pressure compressor;
• and
• a buffer air assembly including:
• a low-pressure header connected to at least one low-pressure bearing compartment and the low-pressure compressor, and the low-pressure header is configured to receive a low-pressure bleed air from the low-pressure compressor;
• a high-pressure header connected to at least one high-pressure bearing compartment and the high-pressure compressor, and the high-pressure header is configured to receive a high-pressure bleed air from the high-pressure compressor;
• and
• at least one electric buffer compressor configured to direct pressurized buffering air to the low-pressure header and the high-pressure header.

A buffer air assembly for an aircraft engine, the buffer air assembly comprising:

• a first pressurized air header;
• at least one first bearing compartment connected in fluid communication with the first pressurized air header;
• a first bleed air source connected in fluid communication with the first pressurized air header, and the first bleed air source is configured to direct first pressurized bleed air to the first pressurized air header;
• a second pressurized air header;
• at least one second bearing compartment connected in fluid communication with the second pressurized air header;
• a second bleed air source, different than the first bleed air source, connected in fluid communication with the second pressurized air header, and the second bleed air source is configured to direct first pressurized bleed air to the first pressurized air header;
• and
• at least one electric buffer compressor configured to direct pressurized buffer air to the first pressurized air header and the second pressurized air header.