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首页> 外文会议>11th annual international energy conversion engineering conference >Numerical and experimental study of the effect of momentum-flux ratio on temperature uniformity at the combustor
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Numerical and experimental study of the effect of momentum-flux ratio on temperature uniformity at the combustor

机译：动量-通量比对燃烧室温度均匀性影响的数值和实验研究

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Gas turbines are used in power production and aerojet propulsion, where the required form of energy is obtained by burning fuel, whether it is propulsion of an aircraft or simply electricity for our homes. Burning of fuels is accompanied by high temperature combustion products that must flow through a gas turbine to generate the power. These products are diluted with lower temperature air to reach the desirable temperature that the turbine blade can withstand. Even after mixing, the temperature of the flow is not very uniform and some hot spots in the flow may cause thermal stresses on the turbine blades. The present paper reports a research project that examined the effect of varying the jet-to-mainstream momentum flux ratio on the temperature uniformity at the exit of a gas turbine combustor through both experimental and computational studies. A combustor simulator was designed to analyze the dilution process and improve mixing such that the first stage turbine blades are subjected to minimal non-uniformities. The experimental results were used to validate the computational model; thereafter, the designs were varied computationally to increase the jet-to-mainstream momentum flux ratio. The results indicate that, with the increase in the jet-to-mainstream momentum flux ratio, there is an improvement in the uniformity of temperature at the combustor exit. One possible reason for this improved temperature uniformity can be attributed to the increased velocity of the dilution jet due to the decreased dilution hole size. Thus, the dilution jets are forced into the mainstream flow, causing better mixing that leads to a flow with more uniform temperature.
机译：燃气轮机用于发电和喷气推进，通过燃烧燃料获得所需形式的能量，无论是推进飞机还是为家庭供电。燃料燃烧伴随着高温燃烧产物，这些燃烧产物必须流经燃气轮机才能发电。这些产品用较低温度的空气稀释，以达到涡轮机叶片可以承受的理想温度。即使在混合之后，流的温度也不是很均匀，流中的一些热点可能会在涡轮叶片上引起热应力。本论文报告了一项研究项目，该项目通过实验和计算研究，研究了改变射流与主流动量通量比对燃气轮机燃烧室出口温度均匀性的影响。设计了燃烧室模拟器来分析稀释过程并改善混合，以使第一级涡轮机叶片受到的不均匀性降至最低。实验结果验证了计算模型的正确性。此后，通过计算改变设计以增加射流与主流的动量通量比。结果表明，随着射流与主流动量通量比的增加，燃烧室出口处的温度均匀性得到改善。这种改善的温度均匀性的一个可能的原因可以归因于由于减小的稀释孔尺寸而导致的稀释射流的速度增加。因此，稀释射流被迫进入主流，导致更好的混合，从而导致温度更均匀的流。

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