精益航空燃气轮机燃烧器的缩放

IF 1.4 4区 工程技术 Q3 ENGINEERING, MECHANICAL
Simon Gövert, Pascal Gruhlke, Thomas Behrendt, Bertram Janus
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引用次数: 0

摘要

摘要提出了一种针对不同推力等级的航空燃气轮机燃烧室瘦身的数值计算方法。该程序考虑了多个操作点,并旨在获得相对于参考配置的自相似流场。开发的缩放方法依赖于基于优化的工作流,该工作流包括自动几何和网格生成、非定常reynolds -average Navier-Stokes (URANS)模拟和后处理。Kriging被用作元模型来识别新的几何参数集。提出了一种基于压力损失、热释放轴向位置、导风劈裂和燃烧室出口温度分布的标度函数。设计了一种通用的内级稀薄燃烧高压航空燃烧室,作为第一个验证测试案例,其反应流特性与真实燃烧室相当。燃烧器几何形状由23个自由参数参数化,这些参数在缩放过程中改变。应用所开发的程序将燃烧室扩展到一个较低的推力等级,同时考虑多个操作点:起飞、进近和怠速。总共有65种不同的燃烧器变体在缩放程序中进行了评估。最终的燃烧室构型,按比例缩小到较低的推力等级,在标度目标方面与参考构型表现出良好的一致性,并且与排放指标相当接近。将缩放过程集成到未来燃烧系统的设计过程中可以减少所需的设计迭代,从而大大减少开发时间和成本。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Scaling of Lean Aeronautical Gas Turbine Combustors
Abstract A numerical procedure is presented for the scaling of lean aeronautical gas turbine combustors to different thrust classes. The procedure considers multiple operating points and aims for a self-similar flow field with respect to a reference configuration. The developed scaling approach relies on an optimization-based workflow which involves automated geometry and grid generation, unsteady Reynolds-averaged Navier-Stokes (URANS) simulations and post-processing. Kriging is applied as a meta model to identify new sets of geometrical parameters. A scaling function based on pressure loss, axial location of heat release, pilot air split and the temperature profile at the combustor exit is proposed. A generic internally-staged lean-burn high pressure aeronautical combustor has been designed to serve as a first verification test case with reactive flow characteristics comparable to real combustion chambers. The burner geometry is parameterized by 23 free parameters which are altered within the scaling process. The developed procedure is applied to scale the combustor to a lower thrust class considering multiple operating points simultaneously: take-off, approach and idle. In total, 65 different combustor variants have been evaluated within the scaling procedure. The final combustor configuration, scaled to a lower thrust class, shows good agreement to the reference configuration in terms of the scaling targets and reasonably resembles the emission indices. Integrating the scaling procedure into the design process of future combustion systems could reduce the required design iterations and thereby contribute to significantly reduced development times and costs.
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来源期刊
CiteScore
3.80
自引率
20.00%
发文量
292
审稿时长
2.0 months
期刊介绍: The ASME Journal of Engineering for Gas Turbines and Power publishes archival-quality papers in the areas of gas and steam turbine technology, nuclear engineering, internal combustion engines, and fossil power generation. It covers a broad spectrum of practical topics of interest to industry. Subject areas covered include: thermodynamics; fluid mechanics; heat transfer; and modeling; propulsion and power generation components and systems; combustion, fuels, and emissions; nuclear reactor systems and components; thermal hydraulics; heat exchangers; nuclear fuel technology and waste management; I. C. engines for marine, rail, and power generation; steam and hydro power generation; advanced cycles for fossil energy generation; pollution control and environmental effects.
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