Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade
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Hongxin Zhang
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Chi Xu
Abstract
Endwall-pulsed blowing (EPB) is studied for three different excitation waveforms to improve the aerodynamic performance of highly loaded compressors. Some important excitation parameters include the excitation frequency and momentum coefficient, which were analyzed in detail. The results of the EPB are compared with the endwall steady blowing (ESB) case. For EPBs with the three excitation waveforms (Waveforms sine, triangle and trapezoid), excitation frequencies that are equal to an integral multiple of the natural frequency of the vortex shedding are optimal and provide better performances than the ESB with the same time-mean momentum coefficient. Moreover, the EPBs of the three excitation waveforms have significant differences in their aerodynamic performance improvements. The optimal case is achieved by the EPB with Waveform triangle and provides a total pressure loss coefficient with a reduction of 25.64%.
Funding source: National Natural Science Foundation of China 10.13039/501100001809
Award Identifier / Grant number: 52206046
Funding source: Natural Science Foundation of Jiangsu Province 10.13039/501100004608
Award Identifier / Grant number: BK20220903
Funding source: China Postdoctoral Science Foundation 10.13039/501100002858
Award Identifier / Grant number: 2022TQ0150
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: J2019-II- 0020-0041
Funding source: Advanced Jet Propulsion Innovation Center
Award Identifier / Grant number: HKCX2020-02-023
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This work was funded by the National Natural Science Foundation of China (No. 52206046), Natural Science Foundation of Jiangsu Province (No. BK20220903), China Postdoctoral Science Foundation (No. 2022TQ0150), National Science and Technology Major Project (No. J2019-II-0020-0041), and Advanced Jet Propulsion Innovation Center (No. HKCX2020-02-023).
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Conflict of interest statement: The authors have no conflict of interest.
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© 2023 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Experimental and numerical study of flame structure and emissions in a micro gas turbine combustor
- Influence of innovative hydrogen multi strut injector with different spacing on cavity-based scramjet combustor
- Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine
- Probabilistic analysis of maximum mode shape for mistuned blisk
- Gain scheduling control of aero-engine based on mixing polynomial LPV synthesis
- A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models
- Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade
- Expanding the choke margin of a mixed flow compressor stage for a micro gas turbine engine
- Supersonic jet mixing in the presence of two annular co-flow streams
- A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption
- Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle
- Numerical investigation of ice crystal melting characteristic and icing risk in an axial compressor
Articles in the same Issue
- Frontmatter
- Experimental and numerical study of flame structure and emissions in a micro gas turbine combustor
- Influence of innovative hydrogen multi strut injector with different spacing on cavity-based scramjet combustor
- Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine
- Probabilistic analysis of maximum mode shape for mistuned blisk
- Gain scheduling control of aero-engine based on mixing polynomial LPV synthesis
- A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models
- Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade
- Expanding the choke margin of a mixed flow compressor stage for a micro gas turbine engine
- Supersonic jet mixing in the presence of two annular co-flow streams
- A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption
- Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle
- Numerical investigation of ice crystal melting characteristic and icing risk in an axial compressor
