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The Effect of Non-Equilibrium Carbon Monoxide (CO) On Turbine Component Design

非平衡一氧化碳 (CO) 对涡轮机部件设计的影响

基本信息

批准号：
2640762
负责人：
金额：
--
依托单位：
University of Oxford
依托单位国家：
英国
项目类别：
Studentship
财政年份：
2021
资助国家：
英国
起止时间：
2021 至无数据
项目状态：
未结题

来源：
https://gtr.ukri.org/projects?ref=studentship-2640762
关键词：
Effect Non Equilibrium Carbon Monoxide

项目摘要

Modern gas turbines engines are designed to deliver high thrust to weight ratios, range, and efficiencies. To get high efficiencies and thrust to weight ratios, the turbine inlet temperature is raised, and the combustor size is reduced. When the turbine inlet is raised above 2000K, dissociated non-equilibrium CO enters the turbine section. If the combustor length is shortened, the fuel has shorter residence time and there is potential for unburnt hydrocarbons leaving the combustor. The dissociated CO and unburnt hydrocarbons react with the oxygen rich film cooling on the turbine nozzle guide vanes and reduce the blade's cooling effectiveness, and life. Therefore, the aim of this project is to study how these reactive species affect the performance of different cooling hole geometries and how to mitigate the effects of heat release from the chemical reactions. A cold shock tube experimental facility at the OTI will be used to study the chemical kinetics and heat transfer in reactive film cooling. The shock produced by the driver gas is used to heat a driven gas seeded with a highly reactive hydrocarbon, which in turn will be blown over a test section with cooling holes ejecting inert and oxygen rich coolants. Optical and non-optical measurement techniques will be used to visualize the reactions and measure the heat transfer and reaction kinetics on the test section. Numerical methods will be used to augment the experimental methodology.

现代燃气涡轮发动机被设计成提供高推重比、航程和效率。为了获得高效率和推重比，涡轮机入口温度升高，燃烧室尺寸减小。当涡轮机入口升高到2000 K以上时，解离的非平衡CO进入涡轮机段。如果燃烧器长度缩短，燃料具有较短的停留时间，并且存在未燃烧的烃离开燃烧器的可能性。分解的CO和未燃烧的碳氢化合物与涡轮机喷嘴导向叶片上的富氧薄膜冷却反应，并降低叶片的冷却效率和寿命。因此，本项目的目的是研究这些活性物质如何影响不同冷却孔几何形状的性能，以及如何减轻化学反应释放热量的影响。OTI的冷激波管实验装置将用于研究反应膜冷却中的化学动力学和传热。由驱动气体产生的冲击用于加热被驱动气体，该被驱动气体以高反应性烃为种子，该被驱动气体继而将被吹过具有喷射惰性和富氧冷却剂的冷却孔的测试段。光学和非光学测量技术将用于可视化反应，并测量试验段上的传热和反应动力学。数值方法将被用来增强实验方法。