AbstractThe main direction of improvement of gas-turbine plants (GTP) and gas-turbine engines (GTE) is increasing the gas temperature at the'/> Estimation of Efficiency of the Cooling Channel of the Nozzle Blade of Gas-Turbine Engines
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Estimation of Efficiency of the Cooling Channel of the Nozzle Blade of Gas-Turbine Engines

机译：燃气轮机喷嘴叶片冷却通道效率的估算

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AbstractThe main direction of improvement of gas-turbine plants (GTP) and gas-turbine engines (GTE) is increasing the gas temperature at the turbine inlet. For the solution of this problem, promising systems of intensification of heat exchange in cooled turbine blades are developed. With this purpose, studies of the efficiency of the cooling channel of the nozzle blade in the basic modification and of the channel after constructive measures for improvement of the cooling system by the method of calorimetry in a liquid-metal thermostat were conducted. The combined system of heat-exchange intensification with the complicated scheme of branched channels is developed; it consists of a vortex matrix and three rows of inclined intermittent trip strips. The maximum value of hydraulic resistance ξ is observed at the first row of the trip strips, which is connected with the effect of dynamic impact of airflow on the channel walls, its turbulence, and rotation by 117° at the inlet to the channels formed by the trip strips. These factors explain the high value of hydraulic resistance equal to 3.7–3.4 for the first row of the trip strips. The obtained effect was also confirmed by the results of thermal tests, i.e., the unevenness of heat transfer on the back and on the trough of the blade is observed at the first row of the trip strips, which amounts 8–12%. This unevenness has a fading character; at the second row of the trip strips, it amounts to 3–7%, and it is almost absent at the third row. At the area of vortex matrix, the intensity of heat exchange on the blade back is higher as compared to the trough, which is explained by the different height of the matrix ribs on its opposite sides. The design changes in the nozzle blade of basic modification made it possible to increase the intensity of heat exchange by 20–50% in the area of the vortex matrix and by 15–30% on the section of inclined intermittent trip strips. As a result of research, new criteria dependences for the complicated systems of heat exchange intensification were obtained. The design of nozzle blades can be used when developing the promising high-temperature gas turbines.
机译： 摘要 燃气轮机厂（GTP）和燃气轮机（GTE）改进的主要方向是提高燃气温度在涡轮进口处。为了解决该问题，开发了在冷却的涡轮叶片中增强热交换的有希望的系统。为此目的，进行了基本变型中的喷嘴叶片的冷却通道的效率以及在通过液态金属恒温器中的量热法改善冷却系统的结构性措施之后的通道的效率的研究。建立了热交换强化与分支通道复杂方案相结合的系统；它由一个涡流矩阵和三排倾斜的间歇跳闸带组成。在跳闸条的第一行观察到最大的水力阻力ξ，这与气流对通道壁的动态冲击，湍流以及在由通道形成的通道进口处旋转117°的影响有关。旅行带。这些因素解释了第一排防倾板的高水力阻力值等于3.7-3.4。热量测试的结果也证实了所获得的效果，即，在脱扣条的第一行中观察到了叶片背面和叶片槽上传热的不均匀性，为8-12％。这种不均匀性具有褪色的特征。在脱扣带的第二排，它占3–7％，而在第三排几乎没有。在涡流基质区域，叶片后部的热交换强度比低谷高，这可以通过基质肋在其相对两侧的不同高度来解释。基本修改的喷嘴叶片的设计变更使得在涡流矩阵区域内的热交换强度增加了20％至50％，在倾斜的间歇跳闸条带的区域内增加了15％至30％的热交换强度。作为研究的结果，获得了对于复杂的热交换强化系统的新的标准依赖性。开发有前途的高温燃气轮机可以使用喷嘴叶片的设计。

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