Wireless telemetry module system for an aircraft engine

A gas turbine engine, comprising:

• a compressor section;
• a combustor section;
• a turbine section;
• a rotatable engine shaft having a central axis;
• a plurality of sensors configured to produce sensor signals;
• and
• a telemetry module system for mounting on the rotatable shaft having a central axis, wherein the telemetry module system includes:
• a telemetry module (TM) having an annular TM housing, a plurality of transmitters, and a first connectivity board, wherein the TM housing extends axially between a TM first axial end and a TM second axial end and includes a TM central bore, and wherein the shaft is received within the TM central bore, and wherein each transmitter of the plurality of transmitters is configured to produce radio-frequency signals based on a sensor input signal, and wherein the first connectivity board has a ring configuration and is attached to the TM housing at the TM second axial end, and the first connectivity board is in signal communication with the plurality of transmitters;
• and a connector ring (CR) having an annular CR housing and a second connectivity board, wherein the CR housing extends axially between a CR first axial end and a CR second axial end and includes a CR central bore, wherein the shaft is received within the CR central bore, wherein the second connectivity board has a ring configuration and is attached to the CR housing at the CR first axial end, and the second connectivity board is configured to receive the sensor signals;
• and wherein the telemetry module and the connector ring are configured to be disposed in a coupled configuration and in the coupled configuration the first connectivity board is in signal communication with the second connectivity board.