| Summary: | 碩士 === 國立臺灣海洋大學 === 輪機工程學系 === 104 === Gas Turbines are widely used for airplane propulsion, land-base power generation and other industrial applications, such as trains, marines, cars, etc. To satisfy the fast development of advanced gas turbines, the operating temperature must be increased to improve the thermal efficiency and output work of the gas turbine engine. However, the heat transferred to the turbine blade is substantially increased as the turbine inlet temperature is continuously increased. Thus, it is very important to cool the turbine blades for a long durability and safe operation. Cooling the blade must cool the critical region that exposed to the hot gas, such as blade tip, passage, suction and pressure side
of the blade surface.
This paper use the software of several common and typical model in ANSYS® Fluent turbulence model, simulate and calculate the complex flow phenomena movement between the blade and vane, which take the general size of blade, and the temperature and pressure of inlet gas set 1673◦K and 1.5 atm for conducting the turbulence model. According to the results of the pressure and temperature field calculations, summarize, analyze and compare, description of each the model results.
The results show, ANSYS® Fluent turbulence model can be divided into steady and unsteady models, and each model in the result of the calculation of the same blade geometry, although the same roughly, but on the critical region, such as blade tip, the surface of pressure side , the tail of suction side, etc., and still display a real operation state, show the similar temperature trends and pressure filed that can be referenced for blade design.
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