Abstract
This paper presents a model for predicting the reference minimum-loss incidence and deviation angles of a blade arrangement with splitter vanes, which is probably a solution for future ultra-highly loaded axial compressor designs. The motivation of the modeling is to guide the blading design in splittered compressor design processes where the additional splitter vanes must be specially considered. The development of the model is based on a blade performance database from systematic numerical simulations. Basic correlations of the model are firstly proposed, which consider dominant blade geometry parameters related to blade loading, including camber angle and solidity. Secondly, geometric and aerodynamic corrections about orientation parameter, blade maximum thickness, inlet Mach number, and three-dimensional (3D) effects are empirically incorporated into the basic correlations. Eventually, a subsonic 3D splittered rotor is designed using the correlations coupled with the corrections obtained from the validation of the model. The results indicate that the model is able to achieve a good agreement within an error band of ±1.0° for the predictions of both reference minimum-loss incidence and deviation angles, and the rotor designed using the model accomplishes the desired work input and flow deflection.
Highlights
An advantageous compressor design in terms of compactness, weight, and cost is needed for gas turbine engines
Sci.addition, 2017, 7, 283the percent pitch (PP) was varied to examine the effects of circumferential position of splitter vanes (SVs) on profile performances for all of the three cases designed by different incidence rules
The results indicate that the correlations of both reference minimum-loss incidence and deviation angles essentially match the database in a certain error band
Summary
An advantageous compressor design in terms of compactness, weight, and cost is needed for gas turbine engines. In order to achieve this goal, increasing the blade speed ( higher relative inflow Mach number for a rotor) or/and flow deflection ( higher blade surface diffusion for a rotor or stator) can be employed These methods usually cause increased deviation angles and aerodynamic losses under much stronger adverse pressure gradient for the highly loaded blades so that the blade performance tends to deteriorate. It is only when the desired velocity triangles are according to the authors’ knowledge, few studies on the topic have been openly published for the appropriately satisfied that a given work input (for rotors), pressure rise, and flow deflection blades with SVs, except for the work conducted by Tzuoo et al [3]. Considered the variation of deviation angles with the solidity and camber of SVs
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