Heat Transfer Measurements in a Water-Cooled Rocket Combustion Chamber Operated with Oxygen/Methane Mixtures at the Mascotte Test Facility

Lucien Vingert (1) , Philippe Grenard (1) , Frédéric Lévy (1) , Aurélie Nicole (1) , Luc-Henry Dorey (1) , Miguel Martin Benito (2)

1 DMPE, ONERA, Université Paris Saclay (COmUE) [Palaiseau]
2 CNES - Centre National d'Etudes Spatiales - Direction Des Lanceurs.

A test series aimed at investigating wall temperatures and heat fluxes in a subscale rocket engine combustion chamber operated with oxygen and methane was achieved at the Mascotte test facility. A total of nearly one hundred and fifty stabilized operating points were reached, enabling to cover a wide operating domain, ranging from subcritical to supercritical chamber pressures (2 to 7 MPa) and mixture ratios from 1 to 3.5, firstly in gas/gas and then in liquid/gas injection conditions. The influences of geometrical parameters like the injectors diameters governing the momentum flux ratio and the distance between the injectors and the wall were also investigated. Some unexpected behaviors were observed for the liquid/gas cases at subcritical pressures, which are still under investigation and deserve further testing.

Mots clés: OXYGEN/METHANE; LIQUID ROCKET ENGINE; HEAT TRANSFER

Mots clés: TRANSFERTS THERMIQUES

Domaines: Sciences de l'ingénieur [physics]; Physique [physics]

Lucien Vingert, Philippe Grenard, Frédéric Lévy, Aurélie Nicole, Luc-Henry Dorey, et al.. Heat Transfer Measurements in a Water-Cooled Rocket Combustion Chamber Operated with Oxygen/Methane Mixtures at the Mascotte Test Facility. 32nd ISTS & 9th NSAT Joint Symposium, Jun 2019, FUKUI, Japan. ⟨hal-02345107⟩