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Investigating the effect of engine speed and flight altitude on the performance of throttle body injection (TBI) system of a two-stroke air-powered engine

机译：研究发动机速度和飞行高度对两冲程气动发动机节气门喷油（TBI）系统性能的影响

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摘要

Two-stroke engines are one of the most commonly used engines for unmanned aerial vehicle (UAV) propulsion, which has benefits such as high power, low fuel consumption. Before, most of the two-stroke engines used in UAVs were the carburettor, but nowadays, carburettor engines are not suitable for UAVs because of stringent standards such as high flight endurance, tolerance of extreme environmental conditions. Also, the solution to meet these expectations is the use of electronic fuel injection systems. In this study, the performance of the fuel injection system in the throttle body injection (TB1) of the two-stroke air-powered engine with the capacity of 30 cc used in the UAV is investigated. Therefore, the performance of the TBI system and the engine is simulated using the lotus engine simulation (LES) soft-ware. The obtained results (mass flow rate of air and fuel, the pulse width of the injector) are used as the initial and boundary conditions of numerical simulation of the TBI system using computational fluid dynamics (CFD) to simulate and check the airflow and fuel injection in the TB1 system. Design features pressure drop in the throttle body, turbulence, speed-pressure distribution in flow, fuel injection and droplet distribution, and mixing them with air, were analysed in the TB1 system. First, the air flow is simulated in a Samorfeld rotary burner; where the k-w SST turbulence model is found suitable for airflow modelling in the throttle body. In the next step, to validate the fuel injection modelling, a non reactive fuel spray was simulated in Sandia burner, and it is observed that the results of fuel injection modelling using the Kelvin-Helmholtz and Riley-Taylor failure model were well-precise to verify the hypothesis and models used. Then the performance of the TBI system was simulated in various operating conditions (1000, 3000, 6000 and 9000 RPM, flying heights of 0 to 20,000 feet). The results of the study of the effect of engine speed on the pressure drop and turbulence intensity of the flow turbulence showed that with the increase in engine speed from 1000 to 9000, the intensity of the turbulence of the flow in the throttle body was increased. Also, with the increase in engine speed, the power of the recycling area was increased. According to the results, the air pressure in the throttle body will decrease with increasing the height. In the study of the effect of the engine speed on the fuel injection characteristic, it was observed that in the 30 degrees throttle and the high speed due to the presence of strong recycling area, the turbulence intensity was high, and the deviation of the droplets from the direction of injection and the dispersion of droplets was also higher. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：二冲程发动机是用于无人机（UAV）推进的最常用发动机之一，它具有诸如高功率，低油耗的优点。以前，无人机中使用的大多数二冲程发动机都是化油器，但是如今，化油器发动机由于严格的标准（例如高飞行耐久性，对极端环境条件的耐受性）而不适用于无人机。同样，满足这些期望的解决方案是使用电子燃油喷射系统。在这项研究中，研究了无人机使用的容量为30 cc的二冲程气动发动机的节气门喷油（TB1）中燃油喷射系统的性能。因此，使用Lotus引擎仿真（LES）软件对TBI系统和引擎的性能进行了仿真。所得结果（空气和燃料的质量流量，喷射器的脉冲宽度）用作TBI系统数值模拟的初始条件和边界条件，该条件使用计算流体力学（CFD）来模拟和检查气流和燃料喷射在TB1系统中。在TB1系统中分析了设计特征，即节气门体中的压降，湍流，流速中的压力分布，燃料喷射和液滴分布以及将它们与空气混合。首先，在Samorfeld旋转燃烧器中模拟气流；发现k-w SST湍流模型适用于节气门体中的气流建模。在下一步中，为了验证燃料喷射建模，在Sandia燃烧器中模拟了非反应性燃料喷雾，并且观察到，使用Kelvin-Helmholtz和Riley-Taylor破坏模型进行的燃料喷射建模的结果精确到验证假设和使用的模型。然后在各种操作条件下（1000、3000、6000和9000 RPM，飞行高度为0至20,000英尺）模拟了TBI系统的性能。发动机转速对液流湍流的压降和湍流强度影响的研究结果表明，随着发动机转速从1000增加到9000，节气门体中液流的湍流强度增加。另外，随着发动机转速的增加，回收区的功率也增加了。根据结果​​，节气门体内的气压将随着高度的增加而降低。在研究发动机转速对燃油喷射特性的影响时，观察到在30度节气门和高转速下，由于存在强大的回收区域，因此湍流强度很高，并且油滴的偏差也很大。从注入方向和液滴的分散性也较高。 （C）2019 Elsevier Masson SAS。版权所有。

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