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Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor

  • Sribhashyam Krishna Kireeti , Gadepalli Ravikiran Sastry and Santosh Kumar Gugulothu EMAIL logo
Published/Copyright: November 8, 2021
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International Journal of Turbo & Jet-Engines
From the journal International Journal of Turbo & Jet-Engines Volume 40 Issue s1

Abstract

A detailed numerical analysis on a scramjet combustor is carried out by introducing an innovative shaped strut in place of the conventional strut. The design of newly added strut aids in generating intense vorticity which helps in efficient mixing of fuel and oxidizer. The air from the isolator enters the combustor at Mach 2.0, whereas fuel enters from the trailing edge of the strut sonically. In this study the flow dynamics with finite volume approach on commercial software Ansys-Fluent 20.0 to solve the two-dimensional Reynolds average Navier Stokes equation (RANS) with compressible fluid flow by considering the density-based solver with SST k-ε turbulent model. The species transport model with volumetric reaction and finite rate/eddy dissipation turbulence chemistry interaction is adopted to study the combustion phenomena and validated with the experimental results, and it is found that the interaction of the shear shock layer enhances the mixing rate by intensifying turbulence. The modified strut injector’s mixing efficiency is compared to the base strut and observed that with a 40% reduction in length, the modified strut injection technique exhibited a mixing efficiency of >95%. The combustion efficiency is then estimated streamwise, and the plot follows the same pattern as the mixing efficiency with fuel burns down completely when x = 150 mm for the modified strut whereas x = 200 mm for the base strut. This can compact the combustion chamber and increases the thrust-to-weight ratio. So, the innovative strut adopted can improvise the combustion efficiency.

Keywords: innovative strut; scramjet combustor; total pressure loss and combustion efficiency; turbulence
Corresponding author: Santosh Kumar Gugulothu, Department of Mechanical Engineering, National Institute of Technology Andhra Pradesh, Tadepalligudem, West Godavari District, Andhra Pradesh 534 101, India, E-mail:

  1. Author contributions: 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: 2021-10-24
Accepted: 2021-10-29
Published Online: 2021-11-08

© 2021 Walter de Gruyter GmbH, Berlin/Boston

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https://doi.org/10.1515/tjj-2021-0055
Keywords for this article
innovative strut; scramjet combustor; total pressure loss and combustion efficiency; turbulence

Articles in the same Issue

  1. Frontmatter
  2. The International Journal of Turbo and Jet Engines
  3. The aerothermodynamic cycle optimal design of a turbofan engine
  4. Multi-condition design optimization of groove flow control technique in an axial-flow pump
  5. Analysis on impulse characteristics of pulse detonation engine with nozzles
  6. Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
  7. Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
  8. Applicability of correlational data-mining to small-scale turbojet performance map generation
  9. Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
  10. Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
  11. Modeling and analysis of 3D radiative heat transfer in combustor
  12. A creep-fatigue life prediction model considering multi-factor coupling effect
  13. Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
  14. Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
  15. A study on design optimization for compressor blisks
  16. Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
  17. Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
  18. Predicting remaining useful life of turbofan engines using degradation signal based echo state network
  19. Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
  20. Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
  21. Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
  22. Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
  23. Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
  24. Performance enhancement and flow separation control in an S-duct by air injection
  25. Gas dynamic analysis of the modern single shaft gas turbine engine flow path
  26. Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
  27. Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
  28. The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
  29. Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
  30. Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
  31. Research on temperature rise characteristics of end V-groove ring seal
  32. Research on the influence of honeycomb cell blockage on the seal leakage characteristics
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  55. Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
  56. Numerical study of transition process in different zones of a compressor cascade channel
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