舰船燃气轮机高压涡轮动叶多维热耦合设计方法

Multidimensional Thermal Coupling Design of High Pressure Turbine Blades for Naval Gas Turbines

针对舰船燃气轮机复杂高效冷却叶片设计,基于压力修正算法建立冷却叶片一维管网设计方法;通过快速求解可压缩边界层微分方程获得叶片外换热边界,基于参数化的叶片网格生成方法,采用全隐式有限体积的固体导热求解方法,构建了冷却叶片的耦合传热模型,开发了耦合传热计算程序。对某高压涡轮动叶进行多维热耦合设计,确定冷却流路及冷气分布,通过三维气热耦合计算验证了设计方案的可行性,通过对比分析验证了多维热耦合设计方法对主要流通单元的流量、压力误差小于5%,具备较高的工程应用价值。

Aiming at the complex and efficient cooling blade design of naval gas turbine,a one-dimensional fluid network design method for the cooling blade is established based on pressure correction method.The heat transfer boundary of the blade is obtained by solving the compressible boundary layer differential equation quickly.Based on the parameterized and conceptual blade grid generation method,a fully implicit finite volume solid heat conduction solution method is adopted to construct the coupling of the cooling blade.The heat transfer model and the coupled heat transfer calculation program are developed.The multi-dimensional thermal coupling design of a high-pressure turbine blade is carried out to determine the cooling flow path and the distribution of cooling air.Finally,the feasibility of the design are verified.Through comparative analysis,it is verified that the error of flow rate and pressure of main flow units is less than 5%by multi-dimensional thermal coupling design method,which has high engineering application value.