EPSRC ICASE/Rolls Royce - Hydrogen Fuel Flow Control for Zero Carbon propulsion systems

项目简介本项目福尔斯属于EPSRC工程研究领域。该研究项目由牛津大学和罗尔斯·罗伊斯公司根据EPSRC iCase奖励计划联合提供。氢作为飞机推进燃料是实现碳减排的一个潜在途径。氢燃料航空航天推进的一个重大挑战是使用液氢来实现更高的有效载荷/航程。液氢在进入燃烧室之前需要压缩和加热。航空航天对在具有挑战性的工作温度和振动环境中精确稳定和瞬态燃料流量计量的要求推动了对定制创新可靠的低重量解决方案的需求。也有一个潜在的需要调制计量的个别燃烧室燃烧器流量，有几个技术解决方案，目前由于高温environment.The主要目标，该项目是研究新的射流阀的概念与应用的氢燃料流量计量。流体动力学装置利用流体力学现象来控制对象流体（例如氢燃料）的行为，同时消除对任何移动部件的需要。以前的工作着眼于流体分流器和切换涡流阀。本文将研究一种新型的对置射流放大器的工作原理。对置射流放大器的工作原理是：将两股相同流体的射流相互对准，用一股小而强的射流切断来自较大入口的弱射流。虽然已知较小的射流实际上可以切断较大射流的流动（只要射流速度不同），但是射流的大小与所需射流速度之间的确切关系尚不清楚，并且可能决定此类装置的可行性。本研究的第一个目的是验证在一系列条件下该设备的标准版本的性能。由于该装置利用固有不稳定的相对射流，因此将进行详细的计算和实验研究以了解最佳性能。最后，将开发和测试更多的发动机尺寸几何形状。在整个研究过程中，将使用多种工程方法来确定和提高设备的性能。3D打印被用于制作设备原型并评估初始性能。这与计算流体动力学结合使用，以模拟无法用原型设备测试的条件下的性能（例如在非常高的压力下）。分析预测也正在进行与实验和计算研究进行比较。因此，该研究项目将包括：研究对置射流的流体动力学研究设备操作的分析建模规范设备行为的计算建模和低压设施的实验验证。合适的发动机规模设备的初步设计和测试该项目福尔斯EPSRC流体动力学，空气动力学和控制研究领域。

Project DescriptionThis project falls within the EPSRC Engineering research area.The studentship is jointly offered by the University of Oxford and Rolls-Royce under the EPSRC iCase award scheme.Hydrogen as a fuel in aircraft propulsion is one potential avenue in achieving carbon reduction. One of the big challenges for hydrogen fuelled aerospace propulsion is the use of liquid hydrogen to enable higher payload/range aircraft. Liquid Hydrogen requires compression and heating before being metered ahead of introduction in the combustion chamber. Aerospace requirements for accurate steady and transient fuel flow metering in challenging operating temperature and vibration environments drives the need for bespoke innovative reliable low weight solutions. There is also a potential need for modulated metering of individual combustor burner flows where there are few technological solutions present due to high temperature environment.The main objective of this project is to investigate novel fluidic valve concept with the application to hydrogen fuel flow metering. Fluidic devices utilize fluid mechanic phenomena to control the behaviour of a subject fluid (such as hydrogen fuel) while removing the need for any moving parts. Previous work has looked at fluidic diverters and switched vortex valves. This work will research the working principle of a novel opposed jet amplifier deviceThe Opposed Jet Amplifier theoretically works by pointing two jets of the same fluid at each other, using one small but powerful jet to cut off a less powerful jet coming from a larger inlet. While it is known that a smaller jet can in fact cut off the flow of a larger one (as long as the jet velocities are different), the exact relationship between the size of the jets and what jet velocities are required is not yet known and will likely determine the viability of such class of devices. The first aim of this research is to characterise performance of a canonical version of the device under series of conditions. As the device utilises opposing jets that are inherently unstable and so detailed computational and experimental studies will be carried out to understand optimum performance. Finally a more engine scale geometry will be developed and tested.Throughout this research a multitude of engineering methodologies are being used to determine and improve the performance of the device. 3D printing is being used to prototype the device and evaluate initial performance. This is being used in conjunction with computational fluid dynamics to simulate performance at conditions that can't be tested with a prototype device (such as at very high pressures). Analytical predictions are also being carried out to compare with experiments and computational studies. The research project will therefore include:Research into fluid dynamics of opposed jetsInvestigation into analytical modelling of the device operation Computational modelling of the canonical device behaviour and experimental validation on low pressure facilities.Preliminary design of a suitable engine scale device and testingThis project falls within the EPSRC Fluid dynamics, aerodynamics and control research areas.