Year: 2013
Type: article
Abstract: This paper presents multipoint Lean-Direct-Injection (LDI) emissions results for flame tube combustion tests at an inlet pressure of 1034 kPa and inlet temperatures between 835 and 865 K; these are the combustor inlet conditions that the High Speed Research (HSR) program used for supersonic cruise. It focuses on one class of LDI geometry, 9-point swirl-venturi LDI (SV-LDI). Two parameters are compared in this paper: the use of dome air and the swirler blade angle. Dome air is called cooling and is at combustor inlet conditions. Three variations are studied: at the venturi throat, at the dome face, and no at all. Two swirler blade angles are studied: 45deg and 60deg. The HSR 9-point SV-LDI emissions are also compared to a similar 9-point SV-LDI design which was used in the later ultra-efficient engine technology (UEET) program. The HSR and UEET designs cannot be compared directly due to different UEET combustor conditions. Therefore, this paper uses previously published UEET correlation equations to make comparisons. Results show that using a 45deg swirler produces lower NOx emissions than using a 60deg swirler. This is consistent with the later UEET results. The effects of spent depend on swirler angle, spent location, and the test conditions. For the configuration with 45deg swirlers, spent delivers lower NOx emissions when it is injected at the throat. For the 60deg swirler, spent does not have much effect on NOx emissions. These results might be caused by the location and the intensity of the flame recirculation zone.
Authors: Zh. He, Kathleen M. Tacina, Chi-Ming Lee, Robert Tacina, Phil Lee
Language: English
Subfield: Computational Mechanics
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W1866980704