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目的:根据微型燃气轮机的特点及其应用领域,针对其核心部件向心涡轮的设计,提出一体化寻优设计方法,并搭建向心涡轮性能试验台进行试验验证,以期检验一体化设计方法的可靠性,获得微型向心涡轮高转速性能试验方法并解决性能试验中出现的实际问题。创新点:1.一体化设计方法是以向心涡轮气动性能、叶轮材料强度和叶轮整体重量为优化目标的全新寻优设计方法;2.针对悬臂式高速小型轴系解决微型向心涡轮高速试验轴承轴系设计问题。方法:1.搭建和完善包含多个子系统的试验台,并给出轴承设计的结果;2.根据相似理论和微型向心涡轮一体化寻优设计结果,对原型进行模化及涡轮试验件的加工;3.开展微型向心涡轮高速性能试验,针对向心涡轮的通流特性和效率特性进行试验数据采集和结果分析,并评估和验证微型向心涡轮一体化寻优设计方法的可靠性和应用性。结论:1.在满足材料强度和整体重量要求的前提下,叶轮气动性能仍具有较高的水平,可应用于100 k W级微型燃气轮机。2.试验工作验证了本文提出的向心涡轮一体化寻优设计方法的可靠性,发展了微型向心涡轮的综合设计方法,以期在工程领域得到进一步的应用。
OBJECTIVE: According to the characteristics of micro gas turbine and its application fields, an integrated optimization design method is proposed for the design of radial turbine of its core components. The radial turbine performance test bench is set up for test verification in order to test the reliability of the integrated design method To obtain the test method of the performance of mini radial centripetal turbine and to solve the practical problems in the performance test. Innovative points: 1. The integrated design method is based on aerodynamic performance of the radial turbine, impeller material strength and the overall weight of the impeller as a new optimization design optimization objectives; 2. For the cantilever high-speed small shaft to solve micro-radial turbine test Bearing shaft design problems. Methods: 1.To build and perfect a test bed with multiple subsystems, and to give the result of bearing design.2. Based on the similar theory and the micro-centripetal turbine optimization design results, the prototype was modeled and the turbine test pieces Processing; 3. To carry out the micro-centripetal turbine high-speed performance test, for the radial turbine flow characteristics and efficiency characteristics of the experimental data acquisition and results analysis, and to evaluate and verify the micro-centripetal turbine optimization design method of reliability and Applicability. Conclusions: 1. The aerodynamic performance of the impeller is still high enough to meet the material strength and overall weight requirements and can be applied to the 100 kW class micro gas turbine. The experimental work verifies the reliability of the radial turbine integrated optimization design method proposed in this paper and develops a comprehensive design method of miniature radial turbine to further application in engineering field.