Aerothermal Interaction Mechansims in the Outer End Wall Area of Modern High Pressure Turbines

能源市场的重大变化以及航空航天领域在效率、性能和排放方面不断提高的要求，给涡轮发动机的开发带来了新的挑战。为了满足这些要求，在设计过程中必须考虑非定常相互作用机制，并且新的开发必须包含跨组件的相互依赖。特别是，高压涡轮的设计过程受到影响，因为在实际配置下进行详细研究非常困难，甚至不可能，因为高压和高温。该项目旨在对研究涡轮机进行测量。研究的重点是涡轮进口条件、冷却流之间的非定常相互作用，以及它们与外壳旋转叶片之间的相互依赖关系。过去已经分别对该地区的空气热机制进行了研究。涡轮内来流与第一叶片前后机匣冷却和动叶尖端冷却的相互作用尚未得到分析。测量计划在一个在低温和低压下运行的大型涡轮钻机上进行。这使得高分辨率测量技术的应用成为可能。然后可以将结果与数值预测进行比较。此外，除了对机理的详细研究外，还打算对设计和仿真工具进行验证。

Significant changes in the energy market and continuously increasing requirements in terms of efficiency, performance and emissions in the aerospace sector lead to new challenges for turbomachine development. To meet these requirements, unsteady interaction mechanisms must be considered during the design process and new developments must incorporate cross-component interdependencies. In particular, the high pressure turbine design process is affected, since detailed investigations at realistic configurations are very difficult or even impossible due to high pressures and temperatures.This project aims at conducting measurements at a research turbine. The efforts are directed at the unsteady interaction of inlet conditions in the turbine, cooling flows, and their interdependency with rotating blades at the outer casing . Aerothermal mechanisms in that region have been investigated separately in the past. The interaction of incoming flow in the turbine with casing cooling in front of and behind the first vane and the tip cooling of rotor blades was not analyzed yet. Measurements are planned at an up-scaled turbine rig running at low temperature and pressure. This enables the application of high-resolution measurement techniques. Results can then be compared to numerical predictions. In addition, besides a detailed investigation of mechanisms, a validation of design and simulation tools is intended.