Investigation of wing installation effects on the sound field of a model jet engine

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Investigation of wing installation effects on the sound field of a model jet engine ( investigation-wing-installation-effects-sound-field-model-je )

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Chapter2. Theory 17 As the jet is exhausted through two separate, usually axially staggered nozzles with different speed and temperature, a multitude of fluid interfaces and subse- quently potential noise sources is generated. Since turbulence in the mixing pro- cess is responsible for jet noise generation, the sound level can only be reduced by decreasing the turbulence. However, the turbulence occurs far downstream of the nozzle, rendering structural provisions inside the jet itself unfeasible. In- stead, the turbulence generation can be moved upstream by utilizing special mix- ing devices at the nozzle plane. Furthermore, turbulence reduction is possible by decreasing the velocity of the jet, which, assuming constant thrust, can only be accomplished by increasing the mass flow m ̇ 0 and thus the BPR. Figure 2.7 shows the achievable noise reduction by encasing the core flow in a slower bypass flow. Note, how the SPL reduction of the high-frequent upstream source becomes more prominent for decreasing bypass flow velocity. An additional challenge is the low frequency portion of the emitted broadband noise, which is generated with great intensity, but is only affected by atmospheric attenuation to a minor degree. Figure 2.7: Reduction in noise radiation by using a mantling bypass flow of different velocities [33]. Experimental investigation of a LC aeroengine showed two mixing regions down- stream of the nozzle that are primarily responsible for jet noise, Fig. 2.8. The first peak in the SPL occurs in close proximity to the nozzle, likely due to the fan flow

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