Aircraft engine turbulence noise reduction device

Abstract

The invention provides an aeroengine turbulent flow noise reduction device. The aeroengine turbulent flow noise reduction device comprises an inner culvert pipe body, a cone body arranged in an innercavity of the inner culvert pipe body in a sleeving manner, multiple turbulent flow bodies arranged on the wall of the same half part of the inner culvert pipe body and an outer culvert pipe body arranged on the outer side of the inner culvert pipe body in a sleeving manner in a manner of being connected with the turbulent flow bodies. The inner culvert pipe body is composed of a first convergencesegment, a straight segment and a second convergence segment, wherein the straight segment and the second convergence segment are in abut joint with the two ends of the first convergence segment; theabut-joint position between the two convergence segments is arranged in a manner of facing the outer culvert pipe body; the turbulent flow bodies are plate-shaped components, two ends of the turbulent flow bodies are in abut joint with the abut-joint position between the convergence segments and one end of the outer culvert pipe body, the other end of the outer culvert pipe body is away from thesecond convergence segment, and the cone body is coaxially sleeved with one side of the second convergence segment of the inner culvert pipe body. Through the turbulent flow noise reduction device, the inner culvert high-speed airflow deviation is caused by deviation of the inner and outer culvert air flow direction, the transmission path of the spraying flow noise is changed, the flow spraying noise is radiated to the upper portion, the downward radiation is weakened, and the noise reduction effect is improved.

Description

technical field [0001] The invention belongs to the field of aero-engine structural design, in particular to the field of aero-engine nozzles, in particular to an aero-engine turbulence and noise reduction device. Background technique [0002] The International Civil Aviation Organization and civil aviation agencies of various countries have formulated and promulgated strict aircraft noise airworthiness regulations, and engine jet noise is one of the main noise sources of aircraft. For this reason, it is necessary to carry out preliminary research on jet noise reduction for turbofan engines with high bypass ratio. The existing noise reduction scheme surrounds the inner high-speed airflow with the outer low-speed airflow, and plays a shielding role on the noise generated by the inner high-speed airflow, thereby reducing the jet noise of the engine. However, the noise reduction scheme has the following disadvantages: the outer low-speed airflow affects the inner Although the ...

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Problems solved by technology

The existing noise reduction scheme surrounds the inner high-speed airflow with the outer low-speed airflow, and plays a shielding role on the noise generated by the inner high-speed airflow, thereby reducing the jet noise of the engine. However, the noise reduction scheme has the following disadvantages: the outer low-speed airflow affects the inner Although the high-speed airflow has a shielding effect, due to the symmetrical reflection of the noise generated by the high-speed airflow, the shielding effect is poor and the noise reduction effect is weak

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