A numerical analysis of a film-cooled oxygen-methane liquid rocket thrust chamber is performed in this work. Ax- isymmetric Reynolds-Averaged Navier–Stokes reactive simulations are carried out considering different simplified injector arrangements and chemical mechanisms. The radiative wall heat flux is evaluated through a discrete transfer method solver with different sets of participating gaseous species and wall emissivities. The computed wall heat flux, comprehensive of both convective and radiative components, is compared to experimental data with and without film cooling, obtaining satisfactory results.
Convective and radiative wall heat transfer evaluation in film-cooled liquid rocket thrust chambers / Migliorino, MARIO TINDARO; Cocirla, Gianluca; Fabiani, Marco; Grossi, Marco; Bianchi, Daniele; Nasuti, Francesco. - (2023). (Intervento presentato al convegno 74th International Astronautical Congress, IAC 2023 tenutosi a Baku, Azerbaijan).
Convective and radiative wall heat transfer evaluation in film-cooled liquid rocket thrust chambers
Mario Tindaro Migliorino
Primo
;Gianluca Cocirla;Marco Fabiani;Marco Grossi;Daniele Bianchi;Francesco Nasuti
2023
Abstract
A numerical analysis of a film-cooled oxygen-methane liquid rocket thrust chamber is performed in this work. Ax- isymmetric Reynolds-Averaged Navier–Stokes reactive simulations are carried out considering different simplified injector arrangements and chemical mechanisms. The radiative wall heat flux is evaluated through a discrete transfer method solver with different sets of participating gaseous species and wall emissivities. The computed wall heat flux, comprehensive of both convective and radiative components, is compared to experimental data with and without film cooling, obtaining satisfactory results.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
