A novel parametric control method for the compressor blade, full-blade surface method, is proposed in this paper. Compared with traditional has good smoothness and construction convenience while maintaining low-dimensional characteristics, compared semi-blade a larger degree of geometric deformation freedom can account changes both suction pressure surface. only four more parameters each so it ...

design models of multi- stage, axial flow compressor are developed for gas turbine engines. axial flow compressor is one of the most important parts of gas turbine units. therefore, its design and performance prediction are very important. one-dimensional modeling is a simple, fast and accurate method for performance prediction of any type of compressors with different geometries. in this appro...

The performance prediction of axial flow compressors at different speeds and under various pressure ratio conditions are still being developed because of costly empirical experiments. One-dimensional modeling is a simple, fast and accurate method for performance prediction in any type of compressor with different geometries. In this approach, inlet flow conditions and compressor geometry are kn...

Design models of multi- stage, axial flow compressor are developed for gas turbine engines. Axial flow compressor is one of the most important parts of gas turbine units. Therefore, its design and performance prediction are very important. One-dimensional modeling is a simple, fast and accurate method for performance prediction of any type of compressors with different geometries. In this appro...

The mixing-plane method for calculating the three-dimensional flow through multistage turbomachinery is used to perform flutter analysis on a single stage transonic compressor. The turbomachine considered is composed of an inlet guide vane (IGV) and a compressor blade (NASA Rotor 67). The mixing-plane boundary condition enables steady and unsteady computation of the flow through multiple blade ...

Non-uniform inlet flows frequently occur in aircrafts and result chronological distortions of total temperature pressure at the engine inlet. Distorted flow operation axial compressor deteriorates aerodynamic performance, which reduces stall margin increases blade stress levels, turn causes failure. Deep learning is an efficient approach to predict catastrophic failure, its stability for better...

Unsteady flow is highly related to loss and aerodynamic performance degradation in the axial compressor. In this paper, dynamic mode decomposition method was used investigate in-depth structures evolutionary mechanisms of internal field. Four main were observed through field decoupling: oscillation tip leakage vortex (TLV) region, circumferential migration leakage-induced (LIV), rear part (RLV)...