某型航空燃气涡轮发动机高空返航的数值研究

G. Litrico, S. Shrivastava, E. Meeks, Pravin M. Nakod, Fang Xu, Dhanya T., Sivaprakasam Muthuraj
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引用次数: 1

摘要

航空发动机的高空重光能力是决定发动机运行飞行包线的关键要求。美国联邦航空管理局(FAA)和欧盟航空安全局(EASA)的监管要求要求建立飞行中发动机重新启动和遵守发动机性能的高度和空速包线。此外,发动机制造商正在改变燃烧室设计,以满足限制氮氧化物(NOx)排放的激进目标。虽然这些设计变化有助于减少氮氧化物的形成,但它们可能会对高海拔地区的重启能力产生问题。因此,发动机设计过程成为一个目标相互冲突的复杂优化问题。试验台数据可以提供对性能的深入了解;然而,使用测试来探索整个设计空间是具有挑战性的,昂贵的,有时是不可行的。在这种情况下,高保真计算流体动力学(CFD)模拟可以弥补这一差距,因此受到设计师和仿真工程师的广泛评价。这种模拟需要解决流动结构、喷雾分布和点火过程,以准确预测高空重燃。此外,为了正确预测不同操作条件下的照明结果,不需要或只需要有限的参数调整。在这项工作中,进行了数值模拟来预测航空燃气轮机燃烧室在不同条件下的轻燃性能,包括海平面和40000英尺运行。CFD模拟使用非定常RANS方法进行湍流、解适应网格和有限速率动力学的燃烧建模,以跟踪火花事件期间和之后的火焰传播。结果令人鼓舞,并预测了与实验测试的有光/无光结果一致的照明和不照明操作条件的准确行为。本文讨论了仿真方法、最佳实践和得到的结果。
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Numerical Study of High-Altitude Relight for an Aviation Gas-Turbine Engine
The altitude relight capability of an aero-engine is a critical requirement that defines the operational flight envelope of the engine. Regulatory requirements from the Federal Aviation Administration (FAA) and European Union Aviation Safety Agency (EASA) ask to establish the altitude and airspeed envelope for in-flight engine restarting and adherence to engine performance. Further, engine manufacturers are changing combustor designs to meet aggressive goals that limit the emission of nitrogen oxides (NOx). While these design changes help reduce the NOx formation, they can be problematic for restart capabilities at high altitudes. Therefore, the engine design process becomes a complex optimization problem with conflicting goals. Test-rig data can provide insights into the performance; however, using testing to explore the entire design space is challenging, expensive, and sometimes infeasible. In this scenario, high fidelity computational fluid dynamics (CFD) simulations can bridge this gap and are, therefore, widely evaluated by designers and simulation engineers. Such simulations need to resolve flow structures, spray distribution, and ignition processes to predict the high-altitude relight accurately. Moreover, no, or limited parameter adjustments should be required for correctly predicting the relight outcome across different operating conditions. In this work, numerical simulations are performed to predict an aviation gas-turbine combustor’s relight performance, operating under different conditions, including sea level and 40000 ft operation. The CFD simulations are performed using the unsteady RANS approach for turbulence, solution-adaptive meshing, and finite-rate kinetics for the combustion modeling that tracks the flame propagation during and after the spark event. The results are encouraging and predict accurate behavior of lighting and not lighting operating conditions consistent with the light/no-light outcomes from the experimental tests. The simulation methodology, best practices, and obtained results are discussed in this paper.
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