Supersonic jet mixing in the presence of two annular co-flow streams
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Rajkumar S
und
Ethirajan Rathakrishnan
Abstract
The mixing characteristics of a Mach 1.9 jet at three levels of overexpansion, corresponding to nozzle pressure ratio (NPR) 3, 4 and 5, in the presence of a sonic co-flow (secondary flow), which was submerged in a subsonic co-flow (tertiary flow) was studied experimentally. For these NPRs the secondary co-flow is sonic with underexpanded levels and the tertiary flow Mach number was found to be 0.41, 0.71 and 0.85, respectively. The centerline decay results of the primary jet show that the jet mixing is abated by the co-flow, at all levels of expansion. However, in spite of the reduced mixing encountered by the supersonic primary jet, the waves in the jet core are found to be weaker in the presence of co-flows. This may be regarded as an advantage from the shock associated noise point of view, in accordance with Tam’s theory; which states weaker the waves in the core, the lesser is the shock associated noise. The results show that the reduced mixing environment caused by the sonic co-flow alone leads to the jet core elongation of about 20%, 23% and 49%, at NPRs 3, 4 and 5, respectively. The core length of the jet is found to increase by 29%, 46% and 62%, respectively, at NPRs 3, 4 and 5, when both sonic and subsonic co-flow streams are present.
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Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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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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© 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
