基于优化设计方法的超高负荷增压级气动设计

以某常规负荷先进三级增压性能参数为基准,尝试采用一种大弯度低损失叶型,进行超高负荷单级增压气动设计。应用基于遗传算法的优化设计方法,以设计点性能为指标进行转静子三维叶片设计,进一步调整转子叶片积叠线规律以提升稳定工作裕度。数值模拟结果表明:以设计点参数为目标进行优化设计可实现设计点高性能;对此超高载荷转子,叶尖前掠使得转子叶片的载荷后移,叶片前缘载荷降低,可增加转子稳定工作攻角范围,有效提升增压级的裕度;与原始三级设计相比,大弯度设计的单级增压级可达到原设计的压比和稳定裕度,效率明显高于原设计,并且与过渡流道匹配较好,验证了设计方法的可行性。

Aerodynamic Design of an Ultra-Highly Loaded Booster by Optimization Method

Referring to the performance parameters of an advanced three-stage booster, this paper tries to design a new ultra-highly loaded booster with only one stage to replace the original one by applying a new concept of diffusion blade profile with large camber and low flow losses. With the index of performance parameters at design point, an optimization method based on genetic algorithm is used to optimize the rotor blade and stator blade, and the surge margin of the booster is further improved by change the blade stacking line of the rotor blade. It shows that 3-D optimization method can improve the performance parameters at the design point highly. For ultra-highly loaded rotor, forward sweep at rotor blade tip can make the load of the blade move downstream and decrease the load of the leading edge which can increase the tolerance range of attack angle and improve the surge margin of the booster stage. At the design point, the newly designed booster has nearly the same total pressure ratio and surge margin as the original booster and exhibits higher efficiency than the original booster. It can also match well with the transition channel, which verifies the feasibility of the design method.