US Patent 12107923 Gas turbine engine communication gateway with internal sensors

A communication adapter of a gas turbine engine of an aircraft includes an internal sensor system including a plurality of sensors within the communication adapter, a memory system, and processing circuitry. The processing circuitry is configured to receive a plurality of time series data at the communication adapter from an engine control of the gas turbine engine, record a plurality of internal sensor data of the internal sensor system, correlate the time series data with the internal sensor data based on an alignment in time to form an enhanced data set, and transmit the enhanced data set from the communication adapter to an offboard system.