Andreas Schwab, Jonas Peichl, Markus Selzer, Hannah Böhrk, Jens von Wolfersdorf

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-78

Transpiration cooling is considered as an innovative cooling method meeting the demand for efficient
cooling of future rocket engine combustion chambers. In this context an experimental baseline study
with a stacked transpiration cooled setup of four aligned ceramic fiber reinforced carbon (C/C) samples
is investigated in hot gas conditions of THG ≈ 374.15 K and ReDh ≈ 200.000 with a transpiring coolant
blowing ratio of F = 0 − 4% of air. Hereby, the focus is on the investigation of the boundary layer
situation based on the measurement of velocity and temperature profiles with a measurement rake
comprising a pitot tube and a thermocouple. A determination of the friction coefficient cf as well as the
Stanton number St is discussed and implemented for the no blowing and blowing cases. On the basis
of two test cases with different transpiration lengths and starting points of uniform transpiration cooling
a unifying illustration is aimed for the derived momentum and mass transfer parameters. Representations considering the momentum thickness Reynolds number Reδ2 and the enthalpy thickness Reynolds
number Reδh yielded good agreement.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2022
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