Wireless sensor for an aircraft propulsion system

A gas turbine engine, comprising:

• a rotor stage including a plurality of rotors, at least one of the rotors including a blade with an internal compartment;
• an enclosure disposed circumferentially around the rotor stage;
• a primary transducer having a primary coil disposed with the enclosure;
• and
• a secondary transducer having a secondary coil connected to a sensor, which secondary transducer is disposed within the internal compartment of the blade;
• wherein the primary transducer is operable to wirelessly transfer power to the secondary transducer, and wherein the secondary transducer is operable to wirelessly transfer sensor data to the primary transducer.

A rotary wing aircraft, comprising:

• an enclosure;
• a mast extending from the enclosure to a plurality of rotors, at least one of the rotors having a blade with an internal compartment;
• a primary transducer having a primary coil disposed with the enclosure;
• and
• a secondary transducer having a secondary coil connected to a sensor, which secondary transducer is disposed within the internal compartment of the blade;
• wherein the primary transducer is operable to wirelessly transfer power to the secondary transducer, and wherein the secondary transducer is operable to wirelessly transfer sensor data to the primary transducer.