Abstract: An apparatus for detecting pressure in a hollow fan blade of a turbofan gas turbine engine comprises a magnetostriction transducer arranged in a sub chamber of the fan blade which is interconnected to a main chamber. A magnetic coil is arranged in the fan casing of the turbofan remote from the fan blade, and an alternating current is supplied from a supply to the magnetic coil to produce an alternating magnetic field. The alternating magnetic field causes the magnetostriction transducer to generate vibrations in the fan blade and the magnetostriction transducer. A magnetic search coil detects changes in the magnetic field, which corresponds to the vibrations, and a processor analyses the vibrations to determine if there has been a change in the resonant frequency of the vibrations which is indicative of a change in the pressure in the fan blade. The processor supplies a signal to a display or to an alarm. The change in the pressure is indicative that the fan blade is cracked and needs replacing.

Abstract: To analyse its spectrum, a radio signal is beat with an intermediate signal in a heterodyne circuit having a local oscillator sweeping a range of intermediate frequencies. The oscillator signal also beats with the output from a comb generator to produce signals marking intervals in its frequency sweep. The magnitude of the filtered intermediate frequency signal is measured between intervals marked by the frequency interval signals to output a frequency spectrum of the input signal. Preferably, the intermediate frequency signal is filtered in a homodyne demodulating unit employing a further local oscillator tuned to the intermediate frequency. A spectrum data display employs a memory storing the signal magnitudes at successive frequency steps at respective addresses associated with individual frequency steps. The magnitude values are assigned to their addresses by the spectrum frequency interval signals.