Swirl-Venturi Lean Direct Injection Combustion Technology for Low-NOx Aero Gas Turbine Engines

Tacina, Kathleen M

关键词: CONVERGENT-DIVERGENT NOZZLES;    FUEL INJECTION;    COMBUSTION CHAMBERS;    NITROGEN OXIDES;    EMISSION;    GAS TURBINE ENGINES;    DESIGN ANALYSIS;    COMBUSTION;   

RP-ID  :  GRC-E-DAA-TN55621

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

This paper summarizes research on the lean direct injection (LDI) combustor concept for aero-gas turbine combustors. The focus of this paper is one particular family of lean direct injection designs, swirl-venturi lean direct injection (SV-LDI). SV-LDI is characterized by the airpath: an air swirler followed by a converging-diverging venturi. For most SV-LDI configurations, a fuel injector is inserted through the center of the air swirler, with the fuel injector tip at or near the venturi throat. Several design variables were studied. These included fuel injector tip location, air swirler blade thickness, air swirler blade angle, and fuel-air mixer size. Moving the fuel injector tip slightly upstream or downstream of the venturi throat has at most a small impact on NOx emissions. Changing the blade thickness also does not affect NOx emissions. Changing the swirler blade angle has a significant effect on NOx emissions. Decreasing swirler blade angle, and thus decreasing swirl number, decreases the NOx emissions at lower flame temperatures (below about 1800 K). However, the slope of the NOx vs. flame temperature curve is higher for lower swirl numbers. Finally, decreasing the fuel-air mixer size initially decreases NOx emissions. However, there may be an optimum fuel-air mixer size below which NOx emissions do not continue to decrease.