Influence of Hydrogen Temperature on the Acoustics of a Rocket Engine Combustion chamber operated with LOX/H2 at Representative Conditions

Kurzfassung

Since the late 1960s, hydrogen temperature is known to have a significant effect on high frequency combustion instabilities in liquid propellant rocket engines with the propellant combination hydrogen and oxygen. In the framework of experimental investigation of high frequency combustion instabilities at the DLR Institute of Space Propulsion in Lampoldshausen, self-excited combustion instabilities were found in an experimental rocket engine combustor with the propellant combination hydrogen / oxygen at a hydrogen temperature of 95K. In order to analyse the influence of hydrogen temperature on these self-excited combustion instabilities, a hydrogen temperature ramping test run was performed. The hydrogen temperature was varied between 40 and 135K. In agreement with previous test runs, highest amplitudes of the 1T mode were found for hydrogen temperatures around 100K.