Abstract
To realize whether the rules for controlling the blade three-dimensional stacking line in a compressor with conventional loading level could be used for the design of a highly loaded compressor, the effects of three-dimensional bladings in an ultra-highly loaded compressor stage were studied numerically. A low-speed compressor stage (Stage-C) with ultra-high loading coefficient (=0.52) was designed at first. Due to the well-chosen through-flow design parameters accompanied using controlled diffusion airfoil with spikeless leading edge, Stage-C achieved the design goal of loading level with high peak efficiency of about 0.89. However, all the blades in Stage-C were designed with radial stacking lines. And then, Stage-C-three-dimensional was re-designed with non-radial stacking blades based on Stage-C, after which 1-point compressor efficiency profit was achieved. Based on the numerical simulations, the performance change in the two compressors and also the effects of blade three-dimensional stacking were discussed in depth. It was found that the endwall corner separation and secondary flows could be suppressed effectively using endwall bending; however, the blade forward sweep design at the rotor tip failed due to strong rotor–stator coupling effects in the highly loaded compressor stage.
Highlights
In order to overcome this structural imperfection of the Low-Speed Large-Scale Axial Compressor (LSLSAC), the swirl of the inlet guide vanes (IGVs) and outlet flow angle of the stator are designed carefully to make the radial profile of the blade loading uniform enough and the stage reaction ranged in a typical region
It can be seen that the 3D bladings in Stage-C-3D make a very little decrease in static pressure rise coefficient at the DE condition; it increases as the mass flow rate f \ 0.49
Compared to that in Stage-C, the non-radial stacking line designs in Stage-C-3D gain a distinct improvement of the isentropic efficiency at any inlet mass flow rate conditions
Summary
Three-dimensional (3D) blade design techniques play a key role in high-performance compressor designs and have been widely used for industry applications.[1,2,3,4] A large number of experimental and numerical works, concerning the physical mechanics of the performance of different blade 3D design (i.e. non-radial stacking line) methods, such as sweep, dihedral, bow, and lean, have been conducted.[1,2,5,6] the results are much diversified in the literatures, and no consensus of quantitative[7,8] and/or even qualitative[9,10] rules could be found for a certain blade 3D design type, resulting in an absence of widely accepted design criteria for blade 3D designs. It is a 1.5-stage axial compressor comprising three blade rows, that is, inlet guide vanes (IGVs), rotor, and stator. The effects of the representative complex 3D flows, such as endwall boundary layers, blade wakes, tip leakage vortex, blade motion effects, and turbulent mixing and heat transfer effects, in a multi-stage compressor were modeled carefully in the code. This code has been widely validated for different compressor configurations, including both single-stage and multi-stage compressors, which has detailed experimental data. It can be seen clearly that the predicted and measured results agree very well
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