| 不同约束条件下跨声速涡轮叶栅伴随气动优化设计 |
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| 引用本文： | 李佳星,罗佳奇,曹志远.不同约束条件下跨声速涡轮叶栅伴随气动优化设计[J].航空动力学报,2021,36(9):1986-1998. |
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| 作者姓名： | 李佳星 罗佳奇 曹志远 |
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| 作者单位： | 1.浙江大学 航空航天学院，杭州 310027 |
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| 基金项目： | 国家自然科学基金（51676003，51976183，51806174） |
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| 摘 要： | 发展了一种简化的基于无反射边界理论的伴随方程进出口边界条件确定方法，研究了考虑不同约束的叶片气动外形优化设计。研究结果表明:采用流动强耦合的简化伴随方程进出口边界条件确定方法，能够确定精度较高的伴随灵敏度，在不同类型的伴随气动优化设计中均具有较好适用性。无约束的出口质量熵优化后，出口质量熵降低0.253%，流道面积和出口气流角变化较大。分别考虑出口气流角气动约束、流道面积几何约束和同时考虑上述两种约束的影响，优化后出口质量熵分别降低0.176%、0.227%和0.164%，优化后叶片气动性能显著提升，且满足约束条件。改变叶型曲率能有效减弱激波强度，吸力面前段曲率降低时，流动减速、出口气流角增大，吸力面前段曲率变化较小时，出口气流角约束较好。
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| 关 键 词： | 气动优化设计 约束条件 伴随方法 边界条件 涡轮叶栅 |
| 收稿时间： | 2020/11/2 0:00:00 |
Adjoint-based aerodynamic design optimization of transonic turbine cascades considering different constraints |
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| LI Jiaxing,LUO Jiaqi,CAO Zhiyuan.Adjoint-based aerodynamic design optimization of transonic turbine cascades considering different constraints[J].Journal of Aerospace Power,2021,36(9):1986-1998. |
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| Authors: | LI Jiaxing LUO Jiaqi CAO Zhiyuan |
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| Affiliation: | 1.School of Aeronautics and Astronautics，Zhejiang University，Hangzhou 310027，China2.School of Power and Energy，Northwestern Polytechnical University，Xi'an 710129，China |
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| Abstract: | A simplified method based on non-reflecting boundary theory for determining the inlet and outlet boundary conditions of adjoint equations was introduced，by which the aerodynamic design optimization of turbomachinery blade considering different constraints was investigated.The results showed that the simplified adjoint equations strongly coupling with flow under inlet and outlet boundary conditions were sufficiently accurate and applicable in different constrained optimization design.After outlet specific entropy design optimization without constraints，the outlet specific entropy decreased by 0.253%，with varied passage area and outlet flow angle.Considering the constraints of outlet flow angle and passage area separately and the constraints from both of them，the outlet specific entropy after optimization decreased by 0.176%，0.227% and 0.164%，respectively.The aerodynamic performance of the optimized blades was significantly improved，while the optimization constraints were maintained.Moreover，the results demonstrated that changing the curvature of blade profile weakened the shock wave effectively.When the curvature of front portions decreased，the flow velocity decelerated and the outlet flow angle increased，meanwhile when the curvature of front portions changed slightly，the outlet flow angle was constrained better. |
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| Keywords: | aerodynamic design optimization constraint adjoint method boundary condition turbine cascade |
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