Work

Direct Numerical Simulation of Flow and Heat Transfer in a Compressor Blade Passage Across a Range of Reynolds Numbers

Year: 2025

Type: article

Abstract: This study employs Direct Numerical Simulation (DNS) to investigate the flow and heat transfer characteristics in a compressor blade passage at five Reynolds numbers (Re=1.091×105, 1.229×105, 1.367×105, 1.506×105, and 1.645×105). A recent method based on local inviscid velocity reconstruction is applied to define and calculate boundary layer parameters, whereas the Rortex vortex identification method is used to analyze turbulent vortical structures. Results indicate that Re significantly affects separation bubble size, transition location, and reattachment behavior, thereby altering wall heat transfer characteristics. On the pressure surface, separation and early transition are observed at higher Re, with the Nusselt number (Nu) remaining high after transition. On the suction surfaces, separation occurs such that large-scale separation at low Re reduces Nu, while reattachment combined with turbulent mixing at high Re significantly increases Nu. Turbulent vortical structures enhance near-wall fluid mixing through induced ejection and sweep events, thereby promoting momentum and heat transport. As Re increases, the vortical structures become denser with reduced scales and the peaks in heat flux move closer to the wall, thus improving convective heat transfer efficiency.

Source: Aerospace

DOI: 10.3390/aerospace12060563

Authors: Yang Liu, Chenchen Zhao, Lei Zhou, Duo Wang, Hongyi Xu

Institution: Fudan University

Language: English

Topic: Turbomachinery Performance and Optimization

Subfield: Aerospace Engineering

Field: Engineering

Domain: Physical Sciences

Open Access status: gold

Estimated APC paid: $2,896

Funder: Shanghai Municipal Education Commission