开式向心涡轮背部间隙流的研究
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摘要
开式向心涡轮通过削去进口段转子轮盘来降低转子重量及轮盘离心应力,广泛应用于微小型燃气轮机中。受削去轮盘的影响,开式向心涡轮转子在叶片进口段同时存在叶片背部间隙及轮盘背部间隙。背部间隙流使动叶通道内二次流结构变得更加复杂,同时更为严重的是,叶片背部间隙内较高的热负荷及轮盘背部间隙内燃气倒灌现象将对涡轮转子寿命造成不利影响。本文使用数值计算方法,分析开式向心涡轮背部间隙流的流动与传热特性,主要工作内容如下：
1.对开式向心涡轮动叶通道内间隙二次流结构进行研究,同时分析间隙流对出口气动参数的影响。结果发现,叶顶间隙流、叶片背部间隙流及轮盘背部间隙流相互作用,动叶通道内存在复杂的间隙二次流结构。同时,间隙流将会改变出口气流角分布并降低涡轮效率,其对出口气动参数分布存在较大影响。
2.对开式向心涡轮叶片背部间隙内部流场结构进行研究,同时分析叶片背部间隙内部流动机制。结果表明,轮盘顶部径向速度及科氏力突然降低,造成叶片背部间隙进出口压差在低径向位置区域迅速减小。受此影响,叶片背部间隙内泄漏流和刮削流相互作用,此消彼长；间隙内存在复杂的分离、再附、回流及射流等流动现象。
3.在开式向心涡轮叶片背部间隙内部流场结构分析的基础上,对叶片背部区域传热特性进行研究,同时采取措施减小叶片背部热负荷。结果发现,间隙内复杂的传热系数分布主要受泄漏流再附及刮削流射流效应的影响。增加间隙大小虽然将增大泄漏流损失,但是却能降低刮削流射流效应造成的高传热系数；叶片背部吸力面肩壁凹槽能够有效降低间隙内流速及再附强度,从而大幅降低叶片背部传热系数。
4.对开式向心涡轮轮盘背部间隙密封流流动特性进行研究,在不同密封设计方案下,分析轮盘背部间隙密封流对涡轮效率、轴向推力、冷却效率及燃气密封效率的影响。结果表明,选取较大的轮盘直径能够在一定程度上提高涡轮效率,但是较大的轮盘直径不仅将增大涡轮轴向推力,而且还将大幅降低密封流冷却效率及燃气密封效率。在同样的轮盘直径下,径向间隙密封的冷却效率和燃气密封效率高于轴向间隙密封。
Deeply scalloped radial turbine rotors "scallop" their disk to reduce weight and centrifugal stress, and are widely used in modern microturbines. The blade backface clearance and the backface cavity clearance are introduced due to the scalloped disk. The backface clearance flows lead to a complicated secondary flow structure in the blade passage, and what is worse, the high thermal load in the blade backface clearance and the hot gas ingestion in the backface cavity clearance are unfavorable for the turbine rotor durability. In this paper, the flow structure and heat transfer of the backface clearance flows in deeply scalloped radial turbines are numerically investigated, and the main contents are as follow:
1. The secondary flow structure due to the clearance flows in the blade passage is investigated, and their influences on the blade outlet parameters are also discussed. It is found that the tip clearance flow, blade backface clearance flow and backface cavity clearance flow interact with each other and the secondary flow structure in the blade passage is complicated. The clearance flow can affect the flow angle at the outlet and reduce the efficiency which has a great impact on the distribution of blade outlet parameters.
2. The flow structure in the blade backface clearance is investigated and the flow mechanism in the clearance is analyzed. It is shown that the radial velocity and Coriolis force are reduced significantly near the disk rim, and the pressure difference across the blade backface clearance decreases drastically. As a result, the leakage flow and the scraping flow interact with each other in the blade backface clearance, and the complex flow separation, reattachment, recirculation and impingement are also found.
3. Based on the flow structure in the blade backface clearance, the heat transfer in the blade backface region is analyzed, and methods are proposed to reduce the thermal load in this region. It is illustrated that the distribution of heat transfer coefficient in the blade backface clearance is mainly governed by the flow reattachment and impingement. Although the leakage loss increases with increasing the clearance height, a larger clearance height can decrease the high heat transfer coefficient due to the impingement effect of the scraping flow. By using the suction side squealer geometry, the velocity and the flow reattachment in the blade backface clearance decrease, and the heat transfer coefficient on the blade backface is reduced remarkably.
4. The backface cavity clearance flow is investigated and its influence on the turbine efficiency, axial thrust, cooling and sealing effectiveness is analyzed for three sealing geometry schemes. It is found that, although the sealing geometry with a larger disk radius has the relatively higher turbine efficiency, the axial thrust increases and the cooling and sealing effectiveness is very low. With the same disk radius, the sealing geometry with a radial clearance shows a better performance on cooling and sealing effectiveness than that with an axial clearance.
1.对开式向心涡轮动叶通道内间隙二次流结构进行研究,同时分析间隙流对出口气动参数的影响。结果发现,叶顶间隙流、叶片背部间隙流及轮盘背部间隙流相互作用,动叶通道内存在复杂的间隙二次流结构。同时,间隙流将会改变出口气流角分布并降低涡轮效率,其对出口气动参数分布存在较大影响。
2.对开式向心涡轮叶片背部间隙内部流场结构进行研究,同时分析叶片背部间隙内部流动机制。结果表明,轮盘顶部径向速度及科氏力突然降低,造成叶片背部间隙进出口压差在低径向位置区域迅速减小。受此影响,叶片背部间隙内泄漏流和刮削流相互作用,此消彼长；间隙内存在复杂的分离、再附、回流及射流等流动现象。
3.在开式向心涡轮叶片背部间隙内部流场结构分析的基础上,对叶片背部区域传热特性进行研究,同时采取措施减小叶片背部热负荷。结果发现,间隙内复杂的传热系数分布主要受泄漏流再附及刮削流射流效应的影响。增加间隙大小虽然将增大泄漏流损失,但是却能降低刮削流射流效应造成的高传热系数；叶片背部吸力面肩壁凹槽能够有效降低间隙内流速及再附强度,从而大幅降低叶片背部传热系数。
4.对开式向心涡轮轮盘背部间隙密封流流动特性进行研究,在不同密封设计方案下,分析轮盘背部间隙密封流对涡轮效率、轴向推力、冷却效率及燃气密封效率的影响。结果表明,选取较大的轮盘直径能够在一定程度上提高涡轮效率,但是较大的轮盘直径不仅将增大涡轮轴向推力,而且还将大幅降低密封流冷却效率及燃气密封效率。在同样的轮盘直径下,径向间隙密封的冷却效率和燃气密封效率高于轴向间隙密封。
Deeply scalloped radial turbine rotors "scallop" their disk to reduce weight and centrifugal stress, and are widely used in modern microturbines. The blade backface clearance and the backface cavity clearance are introduced due to the scalloped disk. The backface clearance flows lead to a complicated secondary flow structure in the blade passage, and what is worse, the high thermal load in the blade backface clearance and the hot gas ingestion in the backface cavity clearance are unfavorable for the turbine rotor durability. In this paper, the flow structure and heat transfer of the backface clearance flows in deeply scalloped radial turbines are numerically investigated, and the main contents are as follow:
1. The secondary flow structure due to the clearance flows in the blade passage is investigated, and their influences on the blade outlet parameters are also discussed. It is found that the tip clearance flow, blade backface clearance flow and backface cavity clearance flow interact with each other and the secondary flow structure in the blade passage is complicated. The clearance flow can affect the flow angle at the outlet and reduce the efficiency which has a great impact on the distribution of blade outlet parameters.
2. The flow structure in the blade backface clearance is investigated and the flow mechanism in the clearance is analyzed. It is shown that the radial velocity and Coriolis force are reduced significantly near the disk rim, and the pressure difference across the blade backface clearance decreases drastically. As a result, the leakage flow and the scraping flow interact with each other in the blade backface clearance, and the complex flow separation, reattachment, recirculation and impingement are also found.
3. Based on the flow structure in the blade backface clearance, the heat transfer in the blade backface region is analyzed, and methods are proposed to reduce the thermal load in this region. It is illustrated that the distribution of heat transfer coefficient in the blade backface clearance is mainly governed by the flow reattachment and impingement. Although the leakage loss increases with increasing the clearance height, a larger clearance height can decrease the high heat transfer coefficient due to the impingement effect of the scraping flow. By using the suction side squealer geometry, the velocity and the flow reattachment in the blade backface clearance decrease, and the heat transfer coefficient on the blade backface is reduced remarkably.
4. The backface cavity clearance flow is investigated and its influence on the turbine efficiency, axial thrust, cooling and sealing effectiveness is analyzed for three sealing geometry schemes. It is found that, although the sealing geometry with a larger disk radius has the relatively higher turbine efficiency, the axial thrust increases and the cooling and sealing effectiveness is very low. With the same disk radius, the sealing geometry with a radial clearance shows a better performance on cooling and sealing effectiveness than that with an axial clearance.
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