航空发动机核心机适航进近噪声预测

为了满足未来的噪声目标,发展对航空器的噪声预测能力,提出了一种用于发动机核心机适航噪声的计算框架。基于PeartDunn模型和SAE-GE模型分别估算进近状态下涡轮和燃烧室的1/3倍频程远场无量纲化均方声压;并将整合后的核心机噪声修正换算为适航规章要求的有效感觉噪声级;以某型发动机为例,通过算法的预测值与官方实测值对比,验证该算法的相对误差约为2%,可用于适航进近状态下发动机核心机噪声的快速评估,从而便于制造商在设计阶段控制发动机核心机噪声满足适航要求,同时也为适航上提前确定进近噪声适航审定试验起始点提供了一种新的思路。

Aeroengine Core Noise Prediction Based on Airworthiness Approach

In order to achieve future noise targets and develop aircraft noise prediction capabilities, this paper proposes a calculation framework for core engine airworthiness noise. Based on the Peart & Dunn model and SAE-GE model, the far-field mean-square acoustic pressure in 1/3-octave bands for turbine and combustion are estimated respectively; then the integrated core engine noise is corrected and converted into the effective perceived noise level which is required by the airworthiness regulations. Taking a certain engine as an example, the relative error of the algorithm is verified as about 2% by comparing the estimated value of the algorithm with the official measured value, showing that it can be used for fast-calculating the approaching core engine noise, so as to give convenience for the manufacturer to control the aeroengine core noise to meet the airworthiness requirements at the design stage. Meanwhile, it provides a new idea for determining the start point of the approaching noise airworthiness certification test in advance.