Time resolved simulation of particle rebound for erosion calculation in jet aero engines

用于喷气航空发动机腐蚀计算的粒子回弹的时间分辨模拟

• 批准号: 420603919
• 负责人: Professorin Dr.-Ing. Andrea D. Beck
• 金额: --
• 依托单位: Institut für Luftfahrtantriebe (ILA)
• 依托单位国家: 德国
• 项目类别: Research Grants
• 财政年份: 2019
• 资助国家: 德国
• 起止时间: 2018-12-31 至 2022-12-31
• 项目状态: 已结题
• 来源: https://gepris.dfg.de/gepris/projekt/420603919?language=en
• 关键词: Time; resolved; simulation; particle; rebound

In the present research proposal, the mechanical damage to material by the impact of solid particles transported in the surrounding fluid, also known as erosion, is to be investigated. The aim is to improve the performance degradation prediction of turbo aero engines by a combined numerical and experimental approach.The erosive particles enter the gas path of the engines as part of the air flow and damage the components, especially the blades. The eroded geometry leads to deviations in the aerodynamics and thus to a deterioration of the performance of the component. The shape change of the components is determined by the trajectory of the particles. Due to the complex geometries of the gas path of aircraft engines, the exact trajectory of these erosive particles is difficult to predict. The trajectories are determined by aerodynamic forces but also by the rebounding behavior of the particles on the walls of the gas path or the blades. Existing rebound models are not accurate enough or have not been investigated at the particle velocities relevant for turbo aero engines. In addition, the numerical methods currently used in industry only compute the time-averaged flow fields and neglect unsteady, turbulent motion and its effect on particle behavior.Therefore, a combined numerical and experimental research project should clarify this question. We combine our expertise in such way that numerical and experimental investigations validate and control each other. With its existing erosion test rig, the Institute of Aircraft Propulsion Systems will investigate the rebound behavior under typical conditions of a high-pressure compressor of a modern turbojet engine. The results are handed over to the Institute for Aerodynamics and Gas Dynamics. The Institute for Aerodynamics and Gas Dynamics, with its existing numerical flow mechanics software, simulates the flow as well as the particle trajectories. Through intensive exchange of the two institutes, the rebound conditions for flat plates, plates with a leading edge radius and a compressor cascade will be studied numerically and experimentally. The aim is therefore to develop a combined experimental-numerical analysis tool during the project that is capable of predicting rebound and erosion behavior in industrially relevant geometries with up-to date not achieved accuracy.

在本研究提案中，将研究由周围流体中输送的固体颗粒的冲击对材料的机械损伤，也称为侵蚀。为了提高涡轮航空发动机性能退化的预测能力，采用数值模拟和实验相结合的方法，研究了涡轮航空发动机中的侵蚀性颗粒作为气流的一部分进入发动机气道，对发动机部件尤其是叶片造成的损伤。被侵蚀的几何形状会导致空气动力学偏差，从而导致部件性能恶化。组分的形状变化由颗粒的轨迹决定。由于飞机发动机气路的复杂几何形状，这些侵蚀性颗粒的确切轨迹难以预测。轨迹由空气动力决定，但也由气体路径或叶片的壁上的颗粒的反弹行为决定。现有的回弹模型不够准确，或者没有在涡轮航空发动机相关的粒子速度下进行研究。另外，目前工业上使用的数值方法只计算时均流场，忽略了非定常、湍流运动及其对颗粒行为的影响，因此，数值与实验相结合的研究项目应该澄清这一问题。我们将我们的专业知识联合收割机结合在一起，使数值和实验研究相互验证和控制。飞机推进系统研究所将利用其现有的腐蚀试验台，研究现代涡轮喷气发动机高压压气机在典型条件下的回弹行为。结果被移交给空气动力学和气体动力学研究所。空气动力学和气体动力学研究所利用其现有的数值流动力学软件模拟了流动和颗粒轨迹。通过两个研究所的深入交流，将对平板、带前缘半径的平板和压气机叶栅的回弹条件进行数值和实验研究。因此，我们的目标是在项目期间开发一种组合实验-数值分析工具，该工具能够预测工业相关几何形状中的回弹和侵蚀行为，并且具有最新的未达到的精度。