Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2022-03-15 DOI:10.1515/tjj-2022-0008

Hano van Eck, S. J. van der Spuy, T. von Backström

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引用次数: 2

Abstract

Abstract The use of micro gas turbines (MGTs) for once-off and unique applications means that a rapid turnaround design process is required. The development of a MATLAB® application-based program for the initial design and performance analysis of radial and mixed flow compressors is discussed. The program code is based on one dimensional (1D) mean line flow and loss model theory. For verification, 18 test compressors were developed, covering a wide range of design velocities, mass flow rates and meridional exit angles. Predicted performance results were verified using Numeca/FINE™ Turbo software. Initial comparisons between 1D and Computational Fluid Dynamics (CFD) results did not match well. The 1D software over-predicted compressor performance and provided poor choke prediction. Consequently, empirical models to correct these deviations were derived and implemented into the 1D Application code. The updated 1D code provided a mean choke prediction difference of 1.59% compared to an initial 14.98% difference at the design point. Mean total-to-total isentropic efficiency and pressure ratio reduced to differences of 0.74 and 1.24% from values of 11.23 and 9.31% respectively.

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微型燃气轮机混流式压缩机级初始设计一维代码的开发

摘要微型燃气轮机（MGT）用于一次性和独特的应用意味着需要快速的周转设计过程。讨论了基于MATLAB®应用程序的径向和混流式压缩机初始设计和性能分析程序的开发。程序代码基于一维（1D）平均线流量和损失模型理论。为了进行验证，开发了18台试验压缩机，涵盖了广泛的设计速度、质量流量和子午出口角。使用Numeca/FINE验证预测性能结果™ Turbo软件。1D和计算流体动力学（CFD）结果之间的初步比较不匹配。1D软件过度预测了压缩机性能，并提供了较差的阻风门预测。因此，导出了校正这些偏差的经验模型，并将其实现到1D应用程序代码中。与设计点处的初始14.98%的差异相比，更新的1D代码提供了1.59%的平均扼流预测差异。平均总等熵效率和压力比分别从11.23%和9.31%降至0.74%和1.24%。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.