Experimental Research on Flow Instability Mechanism of a Highly Loaded Axial CompressorSource: Journal of Engineering for Gas Turbines and Power:;2023:;volume( 145 ):;issue: 009::page 91006-1DOI: 10.1115/1.4062766Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The performance and stable operating range of compressors are critical for the efficient operation of various turbomachinery systems. To reveal the flow instability mechanism of a high-speed and high-loaded compressor, a systematic experimental study on a 1.5-stage high-loaded compressor was conducted in this paper. First, the aerodynamic design and aerodynamic performance evaluation of the compressor were carried out. At 100% corrected speed, the measured choked flowrate, peak efficiency, and stall margin were 4.59 kg/s, 87.1% and 17.5%, respectively. Second, the flow instability mechanism of the highly loaded compressor at different corrected speeds was clarified through the experiments. At 50% corrected speed, the compressor rotor developed from a spike-wave stall precursor to a rotating stall; at 70% corrected speed, the compressor developed directly from a spike-wave precursor to surge; at 90% corrected speed, the compressor has undergone the process of modal wave precursor, spike-wave precursor, and surge. Further, at 70% and 90% corrected speed, a classic surge occurred with surge frequencies of 11.91 Hz and 9.59 Hz, respectively. Through the analysis of short-time power spectrum maximum amplitude, the warning time for the surge was 6.7 ms and 15.6 ms, respectively. Finally, as the compressor throttles to stall/surge conditions, the degree of fluctuation of the autocorrelation coefficient and cross-correlation coefficient increases.
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contributor author | Huang, Song | |
contributor author | Han, Ge | |
contributor author | Yang, Chengwu | |
date accessioned | 2023-11-29T18:42:14Z | |
date available | 2023-11-29T18:42:14Z | |
date copyright | 7/27/2023 12:00:00 AM | |
date issued | 7/27/2023 12:00:00 AM | |
date issued | 2023-07-27 | |
identifier issn | 0742-4795 | |
identifier other | gtp_145_09_091006.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl1/handle/yetl/4294330 | |
description abstract | The performance and stable operating range of compressors are critical for the efficient operation of various turbomachinery systems. To reveal the flow instability mechanism of a high-speed and high-loaded compressor, a systematic experimental study on a 1.5-stage high-loaded compressor was conducted in this paper. First, the aerodynamic design and aerodynamic performance evaluation of the compressor were carried out. At 100% corrected speed, the measured choked flowrate, peak efficiency, and stall margin were 4.59 kg/s, 87.1% and 17.5%, respectively. Second, the flow instability mechanism of the highly loaded compressor at different corrected speeds was clarified through the experiments. At 50% corrected speed, the compressor rotor developed from a spike-wave stall precursor to a rotating stall; at 70% corrected speed, the compressor developed directly from a spike-wave precursor to surge; at 90% corrected speed, the compressor has undergone the process of modal wave precursor, spike-wave precursor, and surge. Further, at 70% and 90% corrected speed, a classic surge occurred with surge frequencies of 11.91 Hz and 9.59 Hz, respectively. Through the analysis of short-time power spectrum maximum amplitude, the warning time for the surge was 6.7 ms and 15.6 ms, respectively. Finally, as the compressor throttles to stall/surge conditions, the degree of fluctuation of the autocorrelation coefficient and cross-correlation coefficient increases. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Experimental Research on Flow Instability Mechanism of a Highly Loaded Axial Compressor | |
type | Journal Paper | |
journal volume | 145 | |
journal issue | 9 | |
journal title | Journal of Engineering for Gas Turbines and Power | |
identifier doi | 10.1115/1.4062766 | |
journal fristpage | 91006-1 | |
journal lastpage | 91006-12 | |
page | 12 | |
tree | Journal of Engineering for Gas Turbines and Power:;2023:;volume( 145 ):;issue: 009 | |
contenttype | Fulltext |