Aeroacoustic Scaling of a Compressor Stator Blade Row

压缩机定子叶片排的气动声学缩放

• 批准号: 468455167
• 负责人: Professor Dr.-Ing. Jörg Seume
• 金额: --
• 依托单位: Institut für Turbomaschinen und Fluid-Dynamik (TFD)
• 依托单位国家: 德国
• 项目类别: Research Grants
• 资助国家: 德国
• 项目状态: 未结题
• 来源: https://gepris.dfg.de/gepris/projekt/468455167?language=en
• 关键词: Aeroacoustic; Scaling; Compressor; Stator; Blade

Economic and regulatory requirements imposed on turbomachinery components of modern turbojet engines have been becoming more stringent over the last decades. The consideration of noise emissions in early development stages is thus becoming an increasingly important design criterion. In the industry, the modelling applied for this purpose is usually based on analytical or empirical approaches, which assume an abstraction of the blade rows, e.g. as flat plates. The validation of these models, but also of numerical tools in later design stages, based on experimental reference data is complicated by the fact that the common turbomachinery test rigs cannot be used for high-quality acoustic measurements due to acoustically unsuitable boundary conditions (low signal-to-noise ratio, high acoustic reflections within the measuring section).On the other hand, acoustically optimized test rigs are only available in selected designs and configurations. For the use of these acoustic test rigs, a similarity assessment is necessary, which allows a comparison between real machines and the test rig environments with controllable acoustic boundary conditions. To achieve this aeroacoustic similarity, approaches based on analytical methods already exist, but so far, they have only been validated with simplified numerical methods. The aim of the project is therefore to extend an existing scaling approaches and to validate them in extensive numerical and experimental investigations. As a practical application, the aeroacoustic similarity of a stator blade row between the high-speed axial compressor and the acoustic wind tunnel of the TFD will be established and investigated. Based on the high-precision measurements and numerical simulations, the validation of the scaling approach will be carried out in order to enable an easier transfer of experimental acoustic investigations to aero engines and stationary turbomachinery in the long term.

在过去的几十年中，对现代涡轮喷气发动机的涡轮机械组件施加的经济和监管要求一直变得越来越严格。因此，在早期开发阶段对噪声排放的考虑已成为越来越重要的设计标准。在行业中，用于此目的的建模通常基于分析或经验方法，该方法假设叶片行的抽象，例如作为平板。基于实验参考数据的验证这些模型的验证，以及以下事实，这一事实是复杂的，即常见的涡轮机械测试钻机不能用于高质量的声学测量值，因此在声学上不适合的边界条件引起的高质量的声学测量（由于较低的信号到噪声比率，低信号与噪声比率，在测量部分中选择了高度的声音反射，并且在测试方面进行了优化的测试。为了使用这些声学测试钻机，必须进行相似性评估，这允许在具有可控声性边界条件的真实机器和测试钻机环境之间进行比较。为了达到这种航空声的相似性，基于分析方法的方法已经存在，但是到目前为止，它们仅通过简化的数值方法进行了验证。因此，该项目的目的是扩展现有的规模方法，并在广泛的数值和实验研究中验证它们。作为一种实际应用，将建立和研究高速轴向压缩机和TFD的声风洞之间的定子叶片行的空气声相似性。基于高精度测量和数值模拟，将对缩放方法的验证进行验证，以便在长期内更轻松地将实验性声学研究转移到Aero发动机和固定的涡轮机械。