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首页> 外文会议>ASME Turbo Expo: Turbomachinery Technical Conference and Exposition >ICE CRYSTAL ICING INVESTIGATION ON A HONEYWELL UNCERTIFIED RESEARCH ENGINE IN AN ALTITUDE SIMULATION ICING FACILITY
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ICE CRYSTAL ICING INVESTIGATION ON A HONEYWELL UNCERTIFIED RESEARCH ENGINE IN AN ALTITUDE SIMULATION ICING FACILITY

机译：高度仿真锦绣工具中霍尼韦尔未经认证研究发动机的冰晶锦冰调查

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A Honeywell Uncertified Research Engine was exposed to various ice crystal conditions in the NASA Glenn Propulsion Systems Laboratory. Simulations using NASA's 1D Icing Risk Analysis tool were used to determine potential inlet conditions that could lead to ice crystal accretion along the inlet of the core flowpath and into the high pressure compressor. These conditions were simulated in the facility to develop baseline conditions. Parameters were then varied to move or change accretion characteristics. Data were acquired at altitudes varying from 5 kft to 45 kft, at nominal ice particle Median Volumetric Diameters from 20 μm to 100 μm, and total water contents of 1 g/m~3 to 12 g/m~3. Engine and flight parameters such as fan speed, Mach number, and inlet temperature were also varied. The engine was instrumented with total temperature and pressure probes. Static pressure taps were installed at the leading edge of the fan stator, front frame hub, the shroud of the inlet guide vane, and first two rotors. Metal temperatures were acquired for the inlet guide vane and vane stators 1-2. In-situ measurements of the particle size distribution were acquired three meters upstream of the engine forward fan flange and one meter downstream of the fan in the bypass in order to study particle break-up behavior. Cameras were installed in the engine to capture ice accretions at the leading edge of the fan stator, splitter lip, and inlet guide vane. Additional measurements acquired but not discussed in this paper include: high speed pressure transducers installed at the trailing edge of the first stage rotor and light extinction probes used to acquire particle concentrations at the fan exit stator plane and at the inlet to the core and bypass. The goal of this study was to understand the key parameters of accretion, acquire particle break-up data aft of the fan. and generate a unique icing dataset for model and tool development. The work described in this paper focuses on the effect of particle break-up. It was found that there was significant particle break-up downstream of the fan in the bypass, especially with larger initial particle sizes. The metal temperatures on the inlet guide vanes and stators show a temperature increase with increasing particle size. Accretion behavior observed was very similar at the fan stator and splitter lip across all test cases. However at the inlet guide vanes, the accretion decreased with increasing particle size.
机译：霍尼韦尔未经认证的研究发动机暴露于NASA Glenn推进系统实验室的各种冰晶条件。使用NASA的1D结冰风险分析工具的模拟用于确定可能导致沿芯流路入口和高压压缩机的冰晶增冰的潜在入口条件。这些条件是在设施中模拟的，以开发基线条件。然后改变参数以移动或改变增齿特性。在从5kFT到45 kft的高度下，以标称冰颗粒中间体积直径为0μm至100μm，总水含量为1g / m〜3至12g / m〜3。还改变了发动机和飞行参数，如风扇速度，马赫数和入口温度。该发动机仪表用全温和压力探针。静压水龙头安装在风扇定子，前框架毂，入口导向叶片的护罩的前缘，以及前两个转子。为入口导向叶片和叶片定子1-2获得金属温度。在发动机前进风扇法兰上游采集粒度分布的原位测量，并在旁路中在风扇下游下游，以研究颗粒分解行为。相机安装在发动机中，以捕获风扇定子，分流器唇和入口导向叶片的前缘的冰空间。本文未讨论但未讨论的附加测量包括：安装在第一级转子的后缘的高速压力换能器，并且用于在风扇出口定子平面和入口处获取颗粒浓度和芯和旁路的光消光探针。本研究的目标是了解accretion的关键参数，获得风扇的粒子分手数据。并为模型和工具开发生成一个唯一的结冰数据集。本文描述的工作侧重于粒子分解的影响。发现旁路中风扇下游存在显着的颗粒分解，尤其是初始粒度较大。入口导向叶片和定子上的金属温度随着粒径的增加而显示温度升高。在所有测试用例的扇形定子和分离器唇中，观察到的摄影行为非常相似。然而，在入口导向叶片上，粒径增加降低。

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