Abstract
Blade tip clearance is one of the most important factors affecting the performance and safety of gas turbine. In recent decades, a variety of non-contact measurement methods of blade tip clearance have been developed and applied to aero engine and gas turbine test. However the research regarding the location and quantity of measurement sensors to ensure the most effective measurement, and how to fully analyze and utilize the test data is still rare. In this paper, a mathematical model of tip clearance has been developed. The model has been applied to study the required quantity and location of the sensors. Based on this model, an analysis method of the measured data is established, and the test data of a Dongfang Steam Turbine Co., Ltd. gas turbine is analyzed. The main factors that cause the non-uniform clearance are determined, and an optimization scheme is formed by this method. The results show that this model and method has great value for measurement scheme design, test data analysis and utilization.
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