摘要
对某型燃气轮机复杂矩阵式高温涡轮冷却叶片进行了热流耦合计算及验证。根据原机设计图纸,应用Pro/Engineer对高压涡轮动叶建立真实、无简化的三维模型,采用ANSYS ICEM对模型进行网格划分;热流耦合计算软件为ANSYS CFX 11.0。为了准确计算燃气对金属叶身的换热及冷却空气出口气膜对叶片尾缘的影响,计算采用了热流耦合的方法。涡轮进口主流燃气的温度在1200℃以上,冷却空气温度为450-550℃。在冷却叶片温度场计算中分别采用κ-ε湍流模型、SST湍流模型,对比了采用不同湍流模型时叶片温度场的差别,并根据整机实测结果验证了计算方法的准确性。高压涡轮动叶温度场计算结果可以作为涡轮叶片设计的依据之一,并为强度计算提供依据。
The paper carries out the heat-flow coupling calculation and the verification for a high-temperature turbine cooling blade which is employed in one type of marine gas turbine.This blade adopts complex matrix form.According to the design drawings of original engine,we establishes a real and non-simplified 3D model for high-pressure turbine rotating blade by use of Pro/Engineer software,as well as accomplishes the grid plot for the model by use of ANSYS ICEM software.The software used for heat-flow coupling calculation is ANSYS CFX 11.0.In order to calculate accurately the heat-exchange between the gas and the metal blade,and to calculate the effect of outlet cooling air film on blade tail edge,the method of heat-flow coupling is introduced in this calculation.The temperature of main gas at turbine inlet is above 1 200℃ and the temperature of cooling air is from 450～550 ℃.In the calculation of temperature field for cooling blade,the κ-ε turbulence model and the SST turbulence model are applied respectively.The difference of blade temperatures using different turbulence models is compared.The accuracy of calculating method is verified according to actual measuring results of complete engine.The result of temperature field calculation for high-pressure turbine rotating blade can be regarded as one of the references of turbine blade design.It can also be regarded as the references for strength calculation.
出处
《舰船科学技术》
2010年第8期111-116,共6页
Ship Science and Technology
关键词
燃气轮机
冷却叶片
热流耦合计算
gas turbine
cooling bleed
heat-fluid couple calculation
