Jonas Peichl, Markus Selzer, Hannah Böhrk, Andreas Schwab, Bastian Hammer, Sandra Ludescher, Karl Alexander Heufer

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-95

In a preliminary feasibility study, transpiration cooling in the supersonic flow of a conical laval type
nozzle is investigated. Hot gas flow with the flow conditions of a rocket engine nozzle is created via a
detonation tube combusting hydrogen and oxygen at a stagnation pressure of 30 bar with a hot gas
flow Mach number of Ma = 3.35 at the beginning of the coolant injection. In this context, a variation of
the transpired coolant mass flow rate, using helium as a coolant gas, was conducted. Special emphasis
is laid on the heat flux reduction on both the transpiration cooled segment as well as the solid nozzle
structure in the wake flow. As result, cooling efficiencies of up to 0.85 at the end of the porous sample
could be measured. For the creation of an cooling film, it could be shown that comparably high blowing
ratios are needed for creating a lasting cooling film.

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In Categories: 1.Events, HiSST 2022, Materials and Structures
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