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Direct Numerical Simulation of Supersonic Film Cooling by Tangential Blowing

In: High Performance Computing in Science and Engineering '19

Author

Listed:
  • Johannes M. F. Peter

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics)

  • Markus J. Kloker

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics)

Abstract

Film cooling is an effective method to thermally protect the nozzle extension of rocket engines from the hot exhaust gases. A cool secondary gas is blown into the supersonic hot-gas turbulent boundary layer through a backward-facing step to generate a cooling film that reduces the heat load of the structure. In this work the complex interaction between the hot supersonic main-flow and the coolant stream is investigated using high-order direct numerical simulations (DNS) to gain fundamental understanding of the mixing physics. The cooling gas is injected at a Mach number of 1.8 into the turbulent Mach-3.3 flat-plate boundary-layer at zero pressure gradient. The main gas is steam (gaseous H2O), the cooling gas is helium, and adiabatic wall conditions are used. Results for various blowing ratios F at kept cooling-gas temperature and Mach number are presented. The interaction of the main stream turbulence and the initially laminar cooling film is investigated in detail as well as the evolution of the cooling effectiveness. The common Goldstein correlation formula for the effectiveness is applied, but no satisfying scaling is achieved.

Suggested Citation

  • Johannes M. F. Peter & Markus J. Kloker, 2021. "Direct Numerical Simulation of Supersonic Film Cooling by Tangential Blowing," Springer Books, in: Wolfgang E. Nagel & Dietmar H. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering '19, pages 263-278, Springer.
    • Handle: RePEc:spr:sprchp:978-3-030-66792-4_18
    DOI: 10.1007/978-3-030-66792-4_18
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