The compressor is a critical component of aero-engines.In order to improve the performance,the compressor ratio of singlestage compressor is getting higher and higher,which will lead to high back pressure gradient and...The compressor is a critical component of aero-engines.In order to improve the performance,the compressor ratio of singlestage compressor is getting higher and higher,which will lead to high back pressure gradient and losses.To solve this problem,there are many techniques applied,such as cantilevered stator,tip clearance and slotted airfoils.However,traditional design methods are experience-dependent and time-consuming.This paper proposes a hybrid optimization method to optimize the stacking line of compressor cascade and reduce total pressure loss on both design and off-design conditions.The approach employs various surrogate models and a multi-infill strategy,outperforming traditional optimization methods using a single surrogate model and a single infilling strategy.The results show that compared to the original blade,the optimized blade has a 34.6%lower mass-averaged total pressure loss at the design point,while the static pressure ratio increases by 2.43%.This paper innovatively combines deep learning-based surrogate models,the hybrid optimization algorithm,and the curvaturebased blade shaping method to optimize the blade shape,shorten the blade design time,and ultimately reduce the losses significantly.展开更多
Compared with a straight blade, a unique compressor blade integratedforward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters ofthe two cascades are measured by a five-hole prob...Compared with a straight blade, a unique compressor blade integratedforward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters ofthe two cascades are measured by a five-hole probe at different positions and ink trace flowvisualization is conducted on blade surfaces. The result shows that the swept-curved cascade haslower endwall loss and higher midspan loss as compared with the straight cascade. However, lowerloss is accompanied with lower diffusion factor. Opposite 'C' shape static pressure distribution isestablished on the suction surface of the swept-curved blade, which is helpful for avoiding theaccumulation of low energy fluid in the endwall corner region. Anyhow the studies support theconclusion that the swept-curved blade conduces to not only the reduction of overall loss but alsothe improvement of stable operation in the endwall corner region.展开更多
In this paper,the simultaneous effects of the sweep and lean of the blades in one stage of a transonic compressor on its performance have been investigated.Then,with the help of numerical solution,fluid flows over the...In this paper,the simultaneous effects of the sweep and lean of the blades in one stage of a transonic compressor on its performance have been investigated.Then,with the help of numerical solution,fluid flows over these two modified geometries generated from the original sample were analyzed.Considering the applied constraints,the two generated rotor geometries have different geometrical characteristics;so that in rotor No.1,the blade has a backward sweep and it is less affected by lean,while in the modified rotor No.2,the blade has a forward sweep and it is more affected by lean.In the first sample,it is observed that the stage efficiency increases by 0.5%for operating design,while the stall margin reduces,and the chocking mass flow rate diminishes by 1.5%.Also regarding the second modified blade,the results indicate that the stall margin increases,the choking flow rate at the nominal rotational speed of the stage increases by 0.18%and the stage efficiency increases by 1%.The comparison of numerical results also shows that,in the first modified rotor,the pressure ratio of the stage diminishes by 0.01%;while in the second sample,the pressure ratio of the stage increases by the same amount.These results were then compared with the experimental results,showing a good agreement.展开更多
基金supported by the National Science and Technology Major Project(J2019-II-0017-0038)the Fundamental Research Funds for the Central Universities.
文摘The compressor is a critical component of aero-engines.In order to improve the performance,the compressor ratio of singlestage compressor is getting higher and higher,which will lead to high back pressure gradient and losses.To solve this problem,there are many techniques applied,such as cantilevered stator,tip clearance and slotted airfoils.However,traditional design methods are experience-dependent and time-consuming.This paper proposes a hybrid optimization method to optimize the stacking line of compressor cascade and reduce total pressure loss on both design and off-design conditions.The approach employs various surrogate models and a multi-infill strategy,outperforming traditional optimization methods using a single surrogate model and a single infilling strategy.The results show that compared to the original blade,the optimized blade has a 34.6%lower mass-averaged total pressure loss at the design point,while the static pressure ratio increases by 2.43%.This paper innovatively combines deep learning-based surrogate models,the hybrid optimization algorithm,and the curvaturebased blade shaping method to optimize the blade shape,shorten the blade design time,and ultimately reduce the losses significantly.
文摘Compared with a straight blade, a unique compressor blade integratedforward-swept and positive-curved stacking line is studied experimentally. Aerodynamic parameters ofthe two cascades are measured by a five-hole probe at different positions and ink trace flowvisualization is conducted on blade surfaces. The result shows that the swept-curved cascade haslower endwall loss and higher midspan loss as compared with the straight cascade. However, lowerloss is accompanied with lower diffusion factor. Opposite 'C' shape static pressure distribution isestablished on the suction surface of the swept-curved blade, which is helpful for avoiding theaccumulation of low energy fluid in the endwall corner region. Anyhow the studies support theconclusion that the swept-curved blade conduces to not only the reduction of overall loss but alsothe improvement of stable operation in the endwall corner region.
文摘In this paper,the simultaneous effects of the sweep and lean of the blades in one stage of a transonic compressor on its performance have been investigated.Then,with the help of numerical solution,fluid flows over these two modified geometries generated from the original sample were analyzed.Considering the applied constraints,the two generated rotor geometries have different geometrical characteristics;so that in rotor No.1,the blade has a backward sweep and it is less affected by lean,while in the modified rotor No.2,the blade has a forward sweep and it is more affected by lean.In the first sample,it is observed that the stage efficiency increases by 0.5%for operating design,while the stall margin reduces,and the chocking mass flow rate diminishes by 1.5%.Also regarding the second modified blade,the results indicate that the stall margin increases,the choking flow rate at the nominal rotational speed of the stage increases by 0.18%and the stage efficiency increases by 1%.The comparison of numerical results also shows that,in the first modified rotor,the pressure ratio of the stage diminishes by 0.01%;while in the second sample,the pressure ratio of the stage increases by the same amount.These results were then compared with the experimental results,showing a good agreement.
