A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption
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Wenlei Lian
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Yu Zhu
Abstract
A design for a turbine pre-swirl system with impeller cavity is proposed to improve the quality of cooling air supplied to the turbine blades of an aeroengine. Impeller cavity is analyzed in order to increase the system pressure ratio with a low system power consumption at the system outlet. Theoretical and numerical investigation are used to investigate the flow characteristics in an impeller cavity pre-swirl system. The conclusions in this study indicate that the impeller structure can increases the pressure ratio by changing the power consumption and distribution of the absolute velocity in the impeller cavity and system outlet. To obtain high pressure ratio and low power consumption, the impeller should have a structure with a high outlet installation radius and low outlet angle. The highest increase in the pressure ratio compared with the empty cavity pre-swirl system is 6.4% and the corresponding increase in the power consumption is 2620 W.
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Research funding: None declared.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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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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© 2023 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- 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
Artikel in diesem Heft
- 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
