基于参数化建模的涡轮叶片气热耦合分析方法研究

Turbine blade conjugated heat transfer analysis method based on parametric modeling

关键词:  气冷涡轮  参数化建模  气热耦合  高保真几何模型  叶片冷却

Key words:  Air-cooled turbine  Parametric modeling  Conjugate heat transfer  High-fidelity geometric model  Blade cooling

摘要:

气冷涡轮的出现使得航空发动机涡轮前温度可以进一步提高，促进了高性能航空发动机的飞速发展。然而随着复杂的内部冲击、扰流强化换热、对流气膜、致密气膜喷淋等冷却形式在涡轮部件上得到应用，冷气与燃气之间的相互作用也越发复杂。为对复杂冷却涡轮叶片的流动和传热耦合影响进行快速、精细化评估，本文建立了一种参数化建模方法，针对GE E³高压涡轮一级导向器进行高保真几何建模和气热耦合仿真。分析结果表明，该参数化建模方法可实现复杂气冷涡轮叶片的高保真几何建模，获得较高的气热耦合计算精度。同时通过详细分析获得了大量的涡轮叶片内部流动换热细节，可支撑高温涡轮叶片的精细化设计。

Abstract:

High-performance aeroengine develops rapidly with higher turbine inlet temperature which is supported by air-cooled turbine technology. However，the interaction between cooling-air and gas becomes more and more complex with the application of cooling forms such as internal impact， pin fins， convection film， and film cooling in turbines. A parametric modeling method is proposed for the rapid and refined assessment of the coupling effects of flow and heat transfer on complex cooling turbine blades. The high-fidelity geometric modeling and conjugated heat transfer analysis are carried out for GE E³ high pressure turbine first guide vane. The analysis shows that the parametric modeling method can reproduce complex air-cooled blade structure and obtain high accuracy of conjugated heat transfer calculation. Thus， a lot of details of flow and heat transfer inside the turbine are obtained， which can benefit the refined design of turbine with high inlet temperature.