Session: 15-09 Impingement and Internal Cooling

Paper Number: 125626

125626 - Study on the Impingement Cooling Structure With the Characteristic of Low Flow Resistance 

As an efficient cooling method, the impingement cooling in the mid-chord of the aero-engine turbine vane causes the jet to impact the target plate, resulting in a thin boundary layer near the stagnation point and high heat transfer, which other aero-engine internal cooling technologies cannot achieve. Adding pin fins to the target plate is a standard method to improve impingement cooling, but it reduces the coolant flow area in the impingement chamber to increase the flow resistance. This paper proposes a novel structure with low resistance characteristics by adding V-ribs to the target plate. The flow and heat transfer characteristics of the traditional and novel structures are comparatively studied through numerical simulations and experiments. The Reynolds Averaged Naiver-Stokes (RANS) model is adopted for the 3-D steady-state numerical simulation, and the shear stress transport (SST) γ-θ turbulence model is used for closing the governing equations. The main conclusions are: compared with the traditional structure of placing pin fins to the target plate, arranging V ribs can increase the flow coefficient and surface-averaged Nusselt number by 5% and 7.3%. The jet Reynolds number (Re) and the flow direction pitch of holes are critical factors that affect the heat transfer, and the change in the jet-to-plate distance can significantly influence the flow resistance. The increase in the jet Reynolds number and the reduction in the flow direction pitch of holes enhance the heat transfer on the target plate by increasing the impingement and wall jet velocities respectively, thereby enhancing the scouring effect. The decrease in pressure in the intake chamber and the corresponding decrease in the pressure gradient in the impingement chamber are the main reasons for the decrease in flow resistance caused by the enlargement of the jet-to-plate distance.

Presenting Author: Changwei Li Northwestern Polytechnical University

Presenting Author Biography: He is mainly engaged in the research of advanced cooling technology for aerospace engines and other turbomachinery, and collaborates with other members of the research group on a number of projects related to the heat transfer and cooling of aerospace engine turbine blades.

Authors:

Changwei Li Northwestern Polytechnical University
Tao Guo Northwestern Polytechnical University
Cunliang Liu Northwestern Polytechnical University
Huiren Zhu Northwestern Polytechnical University
Guodong Li Northwestern Polytechnical University
Xinyu Wang Northwestern Polytechnical University
Jiayu Li Northwestern Polytechnical University
Shanjie Liu Northwestern Polytechnical University