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A fast approach for unsteady compressor performance simulation under boundary condition caused by pressure gain combustion
Applied Thermal Engineering ( IF 6.4 ) Pub Date : 2021-06-19 , DOI: 10.1016/j.applthermaleng.2021.117223
Nicolai Neumann , Majid Asli , Niclas Garan , Dieter Peitsch , Panagiotis Stathopoulos

The constant pressure combustion of the Joule cycle is a dominant source of losses in gas turbines. One possible improvement is pressure gain combustion through pulse detonation combustion. However, the total pressure increase is the result of a transient periodic process that can adversely affect the performance of adjoining turbo components. The thermodynamic benefits of pressure gain combustion can thus be undermined by low efficiencies of compressor and turbine. In order to account for such unsteady effects early in the design process, suitable methods are essential. Given 3D-CFD simulations’ undue computational demands, an approach with low computation resources is required for first-order estimates. This paper introduces such an approach based on a 1D-Euler method and demonstrates its applicability. A compressor is simulated with 3D-CFD, which serves as a reference, as well as with the 1D-Euler code employing unsteady outlet boundary conditions that approximate those encountered with pulse detonation combustion. The findings suggest that the 1D-Euler code is able to accurately capture the transient compressor behaviour. Though the relative pressure amplitude at the compressor outlet of 3.6% is attenuated by 90% up to the compressor inlet, it still results in a compressor isentropic efficiency loss of 0.8 percentage points.



中文翻译:

压力增益燃烧引起的边界条件下非定常压气机性能模拟的快速方法

焦耳循环的恒压燃烧是燃气轮机损失的主要来源。一种可能的改进是通过脉冲爆震燃烧进行压力增益燃烧。然而,总压力增加是瞬态周期性过程的结果,该过程会对相邻涡轮部件的性能产生不利影响。因此,压气机和涡轮机的低效率会削弱增压燃烧的热力学优势。为了在设计过程的早期考虑这种不稳定的影响,合适的方法是必不可少的。鉴于 3D-CFD 模拟的过度计算需求,一阶估计需要具有低计算资源的方法。本文介绍了这种基于 1D-Euler 方法的方法并证明了其适用性。使用 3D-CFD 模拟压缩机,它用作参考,以及使用非定常出口边界条件的 1D-Euler 代码,这些条件近似于脉冲爆震燃烧所遇到的情况。研究结果表明,1D-Euler 代码能够准确捕获瞬态压缩器行为。尽管压气机出口处 3.6% 的相对压力幅值在压气机入口处衰减了 90%,但仍会导致压气机等熵效率损失 0.8 个百分点。

更新日期:2021-06-29
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