Affiliation:
1. Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Abstract
To make measurement of end-wall flow between blade rows in a compact multistage configuration possible, a miniature L-shaped five-hole probe was employed in this paper. This compact tip structure, realized by laser-printing instead of the conventional machining technique, reduces the blockage effect of this intrusive measurement on the flow and ensures high spatial resolution. The zonal method is introduced to extend the usable flow angle range up to 60 degrees. A local least-squares interpolation technique is utilized to acquire flow angle and static/total pressure. In order to improve accuracy for the points located at the sector boundary, the overlap region method is included in the interpolation. Additional test data indicate that the maximum error in flow angle is nearly within 1 degree, and the maximum errors of total pressure and static pressure are 0.56% and 1.9% respectively. The application in a low-speed multistage axial compressor indicates that the zonal method can decrease the number of points exceeding the measurable flow range and is of great significance for the end-wall flow measurement, especially for the near-stall condition. Compared with the traditional method, the proportion of available data for the near-stall state measurement was increased by 18% by using the zonal method.
Funder
National Science and Technology Major Project of China
Reference24 articles.
1. Wisler, D.C. (1985). Lectures on Tip Clearance Effects in Axial Turbomachines, Von Karman Institute for Fluid Dynamics.
2. Loss sources and magnitudes in axial-flow compressors;Koch;J. Eng. Gas Turbines Power,1976
3. Low aspect ratio axial flow compressors: Why and what it means;Wennerstrom;J. Turbomach.,1989
4. The Effect of Aspect Ratio on Compressor Performance;To;J. Turbomach.,2019
5. Stalling Pressure Rise Capability of Axial Flow Compressor Stages;Koch;J. Eng. Power,1981