J. Y. Yu
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Research Subjects
J. Y. Yu has a total of 3 co-authors. Here are the top co-authors by number of shared publications:
- Peng Sun
School of Carbon Neutrality Science and Engineering, Anhui University of Science and Technology, Huainan, 232001, China
1 shared publication W. F. Xu
School of Aero-Engine, Shenyang Aerospace University, Shenyang, China
1 shared publication- Wenguang Fu
School of Mechanical Engineering, Dalian University, Dalian 116622, China
1 shared publication
Latest Publications
- 19 June 2023
- Published by Pleiades Publishing Ltd in Fluid Dynamics
- Vol. 58 (4) , 670-683
Effect of a Tip Groove on the Performance of Compressor Linear Cascade
Based on the structural characteristics of bird-wing bifurcation, the blade tip groove structure of a linear compressor cascade for controlling separation of suction corner was studied with the use of numerical calculation. The obtained results indicated that the effects of the tip groove on the aerodynamic performance and the flow field structure could be improved. The tip groove design caused high-pressure fluid to be injected into the corner position of separation, causing the initial corner position of separation to move backward, so the pitchwise and spanwise corner separation to be controlled. Under the conditions of positive angle of incidence, the blade tip groove had a good loss reduction effect. When the angle of incidence was less than the angle of incidence with the minimum loss, the flow loss in the cascade increased by the adoption of the tip groove. The tip groove needed to be installed near the initial position of the corner separation. As in the groove height increases, the suppression effect of the tip groove on the corner separation initially increases and then decreases. When the groove height is equal to 4% of the blade height (H), the flow loss in the cascade reduces by 14.42%.
- 19 June 2023
- Published by Pleiades Publishing Ltd in Fluid Dynamics
- Vol. 58 (4) , 670-683
Effect of a Tip Groove on the Performance of Compressor Linear Cascade
Based on the structural characteristics of bird-wing bifurcation, the blade tip groove structure of a linear compressor cascade for controlling separation of suction corner was studied with the use of numerical calculation. The obtained results indicated that the effects of the tip groove on the aerodynamic performance and the flow field structure could be improved. The tip groove design caused high-pressure fluid to be injected into the corner position of separation, causing the initial corner position of separation to move backward, so the pitchwise and spanwise corner separation to be controlled. Under the conditions of positive angle of incidence, the blade tip groove had a good loss reduction effect. When the angle of incidence was less than the angle of incidence with the minimum loss, the flow loss in the cascade increased by the adoption of the tip groove. The tip groove needed to be installed near the initial position of the corner separation. As in the groove height increases, the suppression effect of the tip groove on the corner separation initially increases and then decreases. When the groove height is equal to 4% of the blade height (H), the flow loss in the cascade reduces by 14.42%.