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.

在过去的几十年里，对现代涡轮喷气发动机的涡轮增压器部件的经济和法规要求变得越来越严格。因此，在早期开发阶段考虑噪声排放正成为越来越重要的设计标准。在工业中，用于此目的的建模通常基于分析或经验方法，其假设叶片排的抽象，例如作为平板。这些模型的验证，以及在后期设计阶段基于实验参考数据的数值工具的验证，由于以下事实而变得复杂：由于声学上不合适的边界条件，普通的声学测试装置不能用于高质量的声学测量（低信噪比，测量部分内的高声反射）。另一方面，声学优化的测试台仅在选定的设计和配置中可用。为了使用这些声学试验台，相似性评估是必要的，这允许在真实的机器和具有可控声学边界条件的试验台环境之间进行比较。为了实现这种气动声学相似性，已经存在基于解析方法的方法，但到目前为止，它们仅用简化的数值方法进行验证。因此，该项目的目的是扩展现有的缩放方法，并在广泛的数值和实验研究中验证它们。作为一个实际应用，将建立和研究高速轴流压气机和TFD的声学风洞之间的静叶排的气动声学相似性。在高精度测量和数值模拟的基础上，将进行定标方法的验证，以便能够更容易地将实验声学研究转移到航空发动机和固定式发动机。