Abstract
Abstract Transpiration cooling is an innovative cooling concept where a coolant is injected through a porous ceramic matrix composite (CMC) material into a hot gas flow. This setting is modeled by a two-domain approach coupling two models for the hot gas domain and the porous medium to each other by coupling conditions imposed at the interface. For this purpose, appropriate coupling conditions, in particular accounting for local mass injection, are developed. To verify the feasibility of the two-domain approach numerical simulations in 3D are performed for two different application scenarios: a subsonic thrust chamber and a supersonic nozzle.
Highlights
We present numerical results for two application scenarios where the two-domain approach is applied to investigate transpiration cooling in a subsonic thrust chamber and a supersonic nozzle
The heat transfer process of a porous medium flow interacting with a hot gas flow is not yet fully understood
The numerical results for the subsonic thrust chamber confirm that the injection pattern has a strong influence on the cooling film and needs to be considered in the technical design of a cooling system
Summary
In order to bring higher loads into orbit, rocket engines have to be designed with significantly higher thrust. Numerical simulations of subsonic hot gas channel flow exposed to transpiration cooling were conducted by Jiang et al [12] and more recently by Liu et al [20]. In [4] we developed a two-domain approach where two solvers for the hot gas flow and the porous medium flow are solved in alternation. Data between those solvers are exchanged at the coupling interface. We perform numerical simulations for two different application scenarios for transpiration cooling: a subsonic thrust chamber and a supersonic nozzle. For the first scenario we investigate the influence of non-uniform mass injection on the cooling film, whereas for the second scenario the challenge lies in the extension of the range of application.
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