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Experimental investigation on mixing characteristics of high speed co-flow jets by using tabbed chevron nozzle

  • Saravanan A. R. , Thanigaiarasu S. EMAIL logo , Rakesh Divvela and Rathakrishnan E.
Published/Copyright: February 11, 2021
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International Journal of Turbo & Jet-Engines
From the journal International Journal of Turbo & Jet-Engines Volume 40 Issue 2

Abstract

The present study investigates the effect of chevron with tab (Tabbed chevron) fixed at the exit of the co-flowing primary nozzle on the mixing characteristics in subsonic and sonic jets. The experiment was conducted for the jet Mach number 0.6 and 0.8. The centerline Mach number decay was calculated for all these jet Mach numbers for the co-flow baseline nozzle, nozzle with chevrons and tabbed chevron (primary flow) nozzle respectively. It was found that tabbed chevron was effective in reducing the potential core length by 88.23% as compared to the chevron nozzle with baseline nozzle. The radial profile also shows that the mixing enhancement by tabbed chevron is better than chevron nozzle.

Keywords: jet spread; mixing enhancement; potential core length; tabbed chevron
PACS: 47.85.lk
Corresponding author: S. Thanigaiarasu, Department of Aerospace Engineering, MIT Campus, Anna University, Chennai, 600 044, India, E-mail:

  1. Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.

  2. Research funding: None declared.

  3. Conflict of interest statement: The authors declare no conflicts of interest regarding this article.

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Received: 2021-01-13
Accepted: 2021-01-19
Published Online: 2021-02-11
Published in Print: 2023-05-25

© 2021 Walter de Gruyter GmbH, Berlin/Boston

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https://doi.org/10.1515/tjj-2020-0043
Keywords for this article
jet spread; mixing enhancement; potential core length; tabbed chevron

Articles in the same Issue

  1. Frontmatter
  2. Characterization of titanium grade 5 alloy compressor blade in a jet engine using advanced materials for optimum thrust production
  3. Numerical investigation of total temperature distortion problem in a multistage fan based on body force approach
  4. Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine
  5. Baseline architecture design for a turboelectric distributed propulsion system using single turboshaft engine operational scenario
  6. Active fault tolerant control of turbofan engines with actuator faults under disturbances
  7. Modeling and mode transition simulation of over-under turbine based combined cycle (TBCC) propulsion system based on inlet/engine matching
  8. Numerical analysis of high temperature gas flow through conical micronozzle
  9. Simulation and analysis of an aero-engine combustor with a slinger fuel injection system
  10. Influence of plasma-chemical products on process stability in a low-emission gas turbine combustion chamber
  11. Influence of nozzle exit geometrical parameters on supersonic jet decay
  12. Experimental investigation on mixing characteristics of high speed co-flow jets by using tabbed chevron nozzle
  13. Study of a new effervescent atomizer design
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