Abstract
The tonal sound emission of a high-pressure turbine stage is investigated numerically. The mean total temperature of the incoming flow is assumed to vary sinusoidally in the azimuthal direction with a temperature amplitude of 9 %. The results show that the sound power emitted in the downstream direction is increased slightly by 0.2 dB at the blade-passing frequency and by a remarkable 2.7 dB at the first harmonic of the blade-passing frequency. The turbine stage consists of a stator with 70 vanes and a rotor with 73 blades while the temperature field in the simulation has 35 periods in the circumference. A non-uniform mean temperature may be a result of the discrete burners inside the annular combustion chamber, a typical situation for an aero-engine.
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