Abstract
Abstract The combustion instability in a propulsion system is a ubiquitous problem. The radial baffles usually installed on the injector faceplate eliminate the combustion instability (acoustic pressure oscillation) in the propulsion system. In this article, the longitudinal baffles are installed on the inner surface of the combustor wall to control the combustion instabilities. The first-order and second-order tangential modes are induced in the experiments. The effects of the parameters of the baffle on the acoustic pressure oscillation in the cylindrical combustor are investigated. The effect of the combustor nozzle on the tangential modes has been systematically investigated. It is concluded that the eigen-frequency and amplitude of the first-order tangential mode decline with the increase in the longitudinal baffle number and height. For the second-order tangential mode, the eigen-frequency and amplitude monotonically increase until a maximum value (four baffles), subsequently decrease with the increase in the baffle number and height. The combustor without the nozzle obtains a lower frequency than that with the nozzle, especially for the low baffle height in the combustor.
Highlights
Performance and stability are two conflicting concerns in the development of new rocket engine combustion
Many researchers have investigated the effect of the radial baffles, which were installed on the injector faceplate (Figure 1), on the acoustic pressure oscillations in propulsion systems [6,7,8]
The results clearly showed that the radial baffle length provided a greater impact on the acoustic pressure oscillations than the radial baffle number
Summary
Performance and stability are two conflicting concerns in the development of new rocket engine combustion. Culick and Yang [1] thought that the high-frequency combustion instabilities were usually considered as the acoustic pressure oscillations These undesirable phenomena, especially for the tangential mode of the high-frequency combustion instabilities, may enhance the heat transfer rates or resonance, resulting in the deterioration of the propulsion performance and even severe damage on the injector faceplate and combustor wall of the power-generating devices such as rocket engines, ramjets and turbojet thrust augmentors. To eliminate these undesirable instabilities, some passive control methods such as radial baffles and acoustic cavities were widely applied. The effect of the nozzle on the tangential acoustic mode is researched
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