BACKGROUND

The subject matter disclosed herein generally relates to gas turbine engine communication systems and, more particularly, to a gas turbine engine communication gateway with internal sensors.

A control system of a gas turbine engine uses multiple configuration control items, such as control software, data, trim updatable values, and the like to control operation of the gas turbine engine and monitor performance of the gas turbine engine. Once a gas turbine engine is deployed in the field, it can be difficult to access data captured and/or computed by the control system and to make updates to the configuration control items. A gas turbine engine can be deployed in the field for an extended service life, such as a period of decades. Computer system technology and communication technology can evolve at a rapid pace adding to the challenges of interfacing with offboard systems as the offboard technology continues to advance during the lifespan of the engine.

BRIEF DESCRIPTION

According to one embodiment, 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 during operation of the gas turbine engine, record a plurality of internal sensor data versus time in the memory system based on the internal sensor system until an end condition is met, 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 based on a transmit condition.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include a housing having a plurality of mounts configured to couple the communication adapter to a fan case of the gas turbine engine.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the housing includes at least one antenna configured to support wireless communication.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the at least one antenna includes a global positioning system antenna.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the time series data includes a combination of aircraft parameters and engine control parameters with at least one time stamp to establish a time base for correlation with the internal sensor data.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the sensors within the communication adapter include one or more of: an accelerometer, a gyroscope, a barometer, and a magnetometer.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the internal sensor data provides one or more of: a position, an orientation, and a g-load coordinated with time stamping.

According to an embodiment, a method includes receiving a plurality of time series data at a communication adapter of a gas turbine engine of an aircraft, where the time series data is received from an engine control during operation of the gas turbine engine. The communication adapter records a plurality of internal sensor data versus time based on an internal sensor system of the communication adapter until an end condition is met. The time series data is correlated with the internal sensor data based on an alignment in time to form an enhanced data set. The enhanced data set is transmitted from the communication adapter to an offboard system based on a transmit condition.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the communication adapter includes a housing having a plurality of mounts configured to couple the communication adapter to a fan case of the gas turbine engine.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the internal sensor system includes a plurality of sensors within the communication adapter, the sensors including one or more of: an accelerometer, a gyroscope, a barometer, and a magnetometer.

According to an embodiment, a gas turbine engine of an aircraft includes a fan section with a fan case, an engine control mounted on the fan case, and a communication adapter mounted on the fan case. The engine control is configured to monitor and control operation of the gas turbine engine in real-time. The communication adapter includes processing circuitry configured to receive a plurality of time series data from the engine control during operation of the gas turbine engine, record a plurality of internal sensor data versus time based on an internal sensor system until an end condition is met, 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 to an offboard system based on a transmit condition.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the communication adapter includes a housing having a plurality of mounts configured to couple the communication adapter to the fan case of the gas turbine engine.

In addition to one or more of the features described above or below, or as an alternative, further embodiments may include where the housing includes at least one antenna configured to support wireless communication, and the at least one antenna includes a global positioning system antenna.

A technical effect of the apparatus, systems and methods is achieved by incorporating communication features and internal sensors to securely interface an engine control system with offboard systems as described herein.

