The effective Modelling of Reverse Transition

逆向转变的有效建模

• 批准号: 2777185
• 金额: --
• 依托单位: University of Cambridge
• 依托单位国家: 英国
• 项目类别: Studentship
• 财政年份: 2022
• 资助国家: 英国
• 起止时间: 2022 至 无数据
• 项目状态: 未结题
• 来源: https://gtr.ukri.org/projects?ref=studentship-2777185
• 关键词: effective; Modelling; Reverse; Transition

The effective Modelling of Reverse TransitionTo combat the emissions impact of the increasing demand in air travel jet engines must be adapted and designed to be more efficient. A large lever of control for this is raising turbine entry temperature (TET) but this often leads to increased cooling requirements of the turbine blade resulting in efficiency loss and little if any overall benefit.Turbine blades are currently cooled by ejecting "cool" air bled from the compressor onto the surface forming a protective low temperature film. This ejection interacts with the developing boundary layer and often leads to transition of the layer to turbulent flow. Recent findings have highlighted this is not always the case. Preventing or delaying film-induced transition would provide benefits to aerodynamic efficiency as well as possible reductions in cooling requirement, in turn boosting cycle efficiency.Experiments have shown that in some cases the boundary layer remains or reverts to laminar behind the ejection holes, the mechanism behind this has been labelled reverse transition. However, there is no available evidence of what the true physical mechanism is.The aims of this project are to uncover the exact progress of the boundary layer behind the cooling holes and the mechanism preventing or reversing transition to turbulence. This will be achieved using high fidelity direct numerical simulations validated with cascade experiment data. The dataset gained will enable an understanding of the physics which can then be used to help improve aircraft emissions. Two outcomes within the project is looking at how we can design to exploit the phenomena and including the understanding in lower order models to be used in routine simulations

反向过渡的有效建模为了应对航空旅行需求不断增长对排放的影响，喷气发动机必须进行调整和设计，以提高效率。一个很大的控制手段是提高涡轮机入口温度（泰特），但这通常会导致涡轮机叶片的冷却需求增加，从而导致效率损失，并且几乎没有任何总体益处。这种喷射与发展中的边界层相互作用，常常导致边界层转变为湍流。最近的调查结果表明，情况并非总是如此。防止或延迟气膜诱导转捩将有利于提高空气动力学效率，并可能降低冷却需求，从而提高循环效率。实验表明，在某些情况下，边界层在喷射孔后保持或恢复为层流，这背后的机制被称为反向转捩。然而，没有可用的证据表明真正的物理机制是什么。本项目的目的是揭示冷却孔后面的边界层的确切进展以及阻止或逆转转变为湍流的机制。这将通过使用叶栅实验数据验证的高保真度直接数值模拟来实现。所获得的数据集将有助于了解物理学，然后可以用来帮助改善飞机排放。该项目的两个成果是研究我们如何设计以利用这些现象，并包括对用于常规模拟的低阶模型的理解