Purpose

In this study, the performance analysis of the split flow turbofan engine with afterburners has been examined using the parametric cycle analysis method. The purpose of this study is to examine how engine performance is impacted by design parameters and flight ambient values and to develop a software in this context.

Design/methodology/approach

Software has been developed using the open-source PYTHON programming language to perform performance analysis. Mach number, compressor/fan pressure ratio, bypass ratio and density were used as parameters. The effects of these variables on engine performance parameters were investigated.

Findings

Parametric cycle analysis has been calculated for different flight conditions in the range of 0–2 M and 0–15,000 m altitude for turbofan engines. With this study, basic data were obtained to optimize according to targeted flight conditions.

Practical implications

As a result of the performance analysis, the association between the flight conditions and design parameters of engine were determined. A software has been developed that can be used in the design of supersonic gas turbine engines for fast and easy simulation of the design parameters.

Originality/value

The variables used in the literature have been analyzed, and the results of the studies have been incorporated into the developed software, which can be used in innovative engine design. Software is capable to be developed further with the integration of new algorithms and models.

中文翻译：

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使用参数环分析涡轮风扇发动机

目的

在本研究中，使用参数循环分析方法对带加力燃烧室的分流式涡轮风扇发动机的性能分析进行了检验。本研究的目的是研究设计参数和飞行环境值如何影响发动机性能，并在此背景下开发软件。

设计/方法论/途径

软件是使用开源 PYTHON 编程语言开发的，用于执行性能分析。马赫数、压缩机/风扇压力比、旁路比和密度被用作参数。研究了这些变量对发动机性能参数的影响。

发现

对涡扇发动机在 0-2 M 和 0-15,000 m 高度范围内的不同飞行条件进行了参数循环分析。通过这项研究，获得了基础数据，以便根据目标飞行条件进行优化。

实际影响

作为性能分析的结果，确定了飞行条件和发动机设计参数之间的关联。已经开发出一种可用于超音速燃气涡轮发动机设计的软件，可以快速、轻松地模拟设计参数。

原创性/价值

对文献中使用的变量进行了分析，研究结果已纳入开发的软件中，可用于创新的发动机设计。通过集成新算法和模型，可以进一步开发软件。