The Heron Fan: Concept Description and Preliminary Aerothermodynamic Analysis

F. Schöning, D. Kožulović
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引用次数: 0

Abstract

The Heron Fan is a new concept of a fuel powered jet engine that does not utilize a conventional core engine. The fan, a single axial compressor of high diameter, creates thrust, similar to a turbofan. Its blades are hollow with inner channels to transport the core air from the hub to the tip, inducing radial compression. The combustion chamber is located in the casing region, either integrated in the blades or in an external ring. After burning, the core air is returned to the blades and is blown out through an expansion device with a large component in circumferential direction. This propels the fan in the opposite direction. The expansion device may be realized by nozzles integrated in the blade trailing edge or by turbine stages integrated in the blade tip region. Subsequently, the core air mixes with the bypass air, which passes the fan axially, and ejects through the main nozzle, producing thrust. To achieve higher compression ratios, it is possible to install core air compressor stages ahead of the fan. The main purpose of this concept is to reduce weight and complexity of the engine, leading to lower production and operating costs. This is achieved by simplifying the engine architecture, integrating the functions and shortening some of the components. In particular, the core engine has been rearranged, thus eliminating the second and in some cases the third shaft. Further, the complete expansion and parts of the compression have been integrated in the fan blade. To assess the aero-thermodynamic parameters, a preliminary cycle analysis has been done, where the most influential parameters were varied. The results show, that the above listed benefits can be achieved while maintaining an efficiency comparable to conventional turbofans. Further, a feasibility study in terms of geometry, internal flow, component implementation and installation has been done, in order to qualify the concept and to identify the most critical aspects. To incorporate the corresponding thoughts and results, as well as to find and eliminate conceptual conflicts and opposing trends, a CAD model has been generated. Overall, the results are sound and encouraging, hence justifying future investigations. However, the Heron Fan concept also brings structural, thermal and aerodynamic challenges which are illustrated and briefly discussed, but still need detailed investigation.
苍鹭扇:概念描述及初步气动分析
“苍鹭扇”是一种新概念的燃料动力喷气发动机,不使用传统的核心发动机。风扇是一个大直径的单轴压气机,产生推力,类似于涡轮风扇。它的叶片是中空的,内部通道将核心空气从轮毂输送到尖端,引起径向压缩。燃烧室位于机匣区域,要么集成在叶片中,要么在外部环中。燃烧后,核心空气返回叶片,并通过具有大组件的周向膨胀装置吹出。这将风扇推向相反的方向。膨胀装置可以通过集成在叶片尾缘的喷嘴或集成在叶尖区域的涡轮级来实现。随后,核心空气与沿轴向通过风扇的旁通空气混合,并通过主喷嘴喷出,产生推力。为了获得更高的压缩比,可以在风扇之前安装核心空压机级。这一概念的主要目的是减轻发动机的重量和复杂性,从而降低生产和运营成本。这是通过简化引擎架构,整合功能和缩短一些组件来实现的。特别是,核心发动机已经重新安排,从而消除了第二轴,在某些情况下第三轴。此外,整个膨胀和部分压缩已经集成在风扇叶片中。为了评估气动热力学参数,进行了初步的循环分析,其中影响最大的参数发生了变化。结果表明,在保持与传统涡扇相当的效率的同时,可以实现上述优点。此外,还进行了几何形状、内部流动、组件执行和安装方面的可行性研究,以确定概念并确定最关键的方面。为了整合相应的思想和结果,以及发现和消除概念冲突和对立趋势,生成了CAD模型。总的来说,结果是合理的和令人鼓舞的,因此证明了未来的研究是合理的。然而,“苍鹭扇”概念也带来了结构、热学和空气动力学方面的挑战,这些挑战已经被简单地阐述和讨论过,但仍需要详细的研究。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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