Fundamental Study of a 7-Element Fuel Injector Configuration for Gas Turbine Combustors, a Look at Cold Flow and Burning Measurements

Hicks, Yolanda R ; Capil, Tyler G ; Anderson, Robert C ; Tacina, Kathleen M

关键词: FUEL INJECTION;    GAS TURBINE ENGINES;    COMBUSTION CHAMBERS;    FUEL COMBUSTION;    COLD FLOW TESTS;    PARTICLE IMAGE VELOCIMETRY;   

RP-ID  :  GRC-E-DAA-TN55619

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

As part of a parametric study in which we vary swirler angle and orientation and look at their effect on fluid mixing and combustion, we examine one configuration of a 7-point lean direct injector by looking at the non-combusting 2-D velocity field using PIV (Particle Image Velocimetry), and combusting system for chemical species using chemiluminescent imaging and flame spectroscopy. The circular 7-point array consists of axial swirlers, with the center 60 degree counterclockwise swirler surrounded by six 52 degree clockwise swirlers. The velocity results for this configuration show that the outer swirlers serve to isolate the center flow field near the injector exit. A recirculation zone forms downstream of the center swirler, but not behind the outer swirlers. The combusting results also show an isolated zone directly downstream of the center injector. The flame spectra show variation in speciation of combustion species such as OH* and CH*, and as a function of position within the combustor.