Abstract
Non-uniform inlet flows frequently occur in aircrafts and result in chronological distortions of total temperature and total pressure at the engine inlet. Distorted inlet flow operation of the axial compressor deteriorates aerodynamic performance, which reduces the stall margin and increases blade stress levels, which in turn causes compressor failure. Deep learning is an efficient approach to predict catastrophic compressor failure, and its stability for better performance at minimum computational cost and time. The current research focuses on the development of a transonic compressor instability prediction tool for the comprehensive modeling of axial compressor dynamics. A novel predictive approach founded by an extensive CFD-based dataset for supervised learning has been implemented to predict compressor performance and behavior at different ambient temperatures and flow conditions. Artificial Neural Network-based results accurately predict compressor performance parameters by minimizing the Root Mean Square Error (RMSE) loss function. Computational results show that, as compared to the tip radial pressure distortion, hub radial pressure distortion has improved the stability range of the compressor. Furthermore, the combined effect of pressure distortion with the bulk flow has a qualitative and deteriorator effect on the compressor.
Highlights
This article is an open access articleFor the last few decades, aerodynamic instability in the transonic axial compression system of commercial and military aero engines is under extensive research
The results found that hub radial pressure distortion and co-swirl flows improve the stability range of turbofan
As stated above the methodologies, this section is divided into three subsections that are based on CFD results, Artificial Neural Network analysis, and regression-based analysis
Summary
For the last few decades, aerodynamic instability in the transonic axial compression system of commercial and military aero engines is under extensive research. Several aircraft engines have witnessed severe operational issues and engine failures due to severe inlet flow distortions. Well-known compressor instability phenomena are rotating stall and surge. Are relying on the flow entrance in compressors. Distortion at the flow entrance creates total pressure non-uniformity at the rotor blades. The non-uniform flow entrance in the compressor may lead to an enormous range of ramifications for the compressor’s operability. All commercial and military aircrafts are frequently endangered by complex inlet flow conditions. Surge and rotating stall are undesirable phenomena that cause mechanical, thermal loads, and structural damages to compressor blades, which decrease compressor efficiency and pressure difference. The engine is required to be restarted the in case of an unrecoverable surge, which has catastrophic outcomes in gas turbine engines
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