MERiT — Methane in Rocket nozzle cooling channels - conjugate heat Transfer measurements

For future rocket propulsion systems it is of strategic importance to develop knowledge of the heat transfer characteristics and material influence at relevant operating conditions. This project will investigate, for different relevant nickel-alloys and typical channel geometries, hydrocarbon fuels and operating conditions to determine: heat transfer coefficient (HTC), degree of coking and corrosion in the cooling channel, pressure loss as a function of supplied heat load, wall temperature, Reynolds number, fuel composition and pressure level.

Funded by:

SNSA (Swedish National Space Agency)

Time period:

20160901 – 20230430

Project partners:

GKN Aerospace Sweden

European Space Agency

Background

Quantitative information on the heat transfer characteristics for nickel-alloy steels under influence of hydrocarbon fuels at high pressure and temperature, as for the cooling of rocket nozzles, is to a high degree unavailable in the open literature. In order to maintain and gain new market shares in future rocket propulsion systems it is of strategic importance that the industry and academia develop necessary knowledge of the heat transfer characteristics and material influence at relevant operating conditions.

Aim and objectives

The objectives with the investigations are, for different relevant nickel-alloys and typical channel geometries, hydrocarbon fuels and operating conditions to determine:

heat transfer coefficient (HTC)
degree of coking and corrosion in the cooling channel
pressure loss as a function of supplied heat load, wall temperature, Reynolds number, fuel composition and pressure level.