Abstract
The role of the primary jets in the aerothermal behavior and overall performance of a gas turbine combustor is explored through an experimental study. The study is performed in a model laboratory combustor that possesses the essential features of practical combustors. The test bed is designed to accommodate optical access for laser diagnostics and overall flow visualization, and is capable of incorporating variable inlet geometries. In the present case, the combustor is operated on JP-4 at atmospheric pressure. A parametric variation in the number of jets per row and axial location of the jet row is performed. The aerodynamic and thermal fields are characterized using laser anemometry and a thermocouple probe, respectively. Species concentrations are acquired via extractive probe sampling. The results demonstrate the importance of primary jet location with respect to the dome swirler. The percent mass recirculated into the dome region, as well as the overall uniformity of mixing and combustion efficiency, are substantially influenced by jet row location. The momentum ratio of the incoming primary jet stream to that of the approaching crossflow of reacting dome gases has a direct impact on the mixing patterns as well. An increase in the number of primary jets leads, in the present case, to more uniform mixing.
Highlights
Substantial interest is directed to gas turbine combustion as a result of (1) a goal to double gas turbine engine performance, (2) the need to create combustor nozzle systems that are fuel flexible, and (3) the initiative to expand combustor technology in support of hypersonic flight.The design of gas turbine combustors is today predicated on empirical data associated with the overall combustion performance of the system
This study delineates the importance and complexities associated with the primary jets in controlling combustor aerothermal behavior, and the overall performance
The relative position of the primary jets to the swirl injection plane is of paramount importance
Summary
Substantial interest is directed to gas turbine combustion as a result of (1) a goal to double gas turbine engine performance, (2) the need to create combustor nozzle systems that are fuel flexible, and (3) the initiative to expand combustor technology in support of hypersonic flight.The design of gas turbine combustors is today predicated on empirical data associated with the overall combustion performance of the system. A model laboratory can combustor is employed with optical access and the essential features of gas turbine combustors (including spray injection, swirl stabilized dome aerodynamics, and wall jet injection). The combustors used in this study are based on a model combustor dubbed the Wall Jet Can Combustor, WJCC, developed at the UCI Combustion Laboratory (Rudoff, 1986). This combustor features dome swirl and two rows of discrete wall jets. In previous work this combustor was characterized via detailed spatial maps of velocity, temperature, and droplet field statistics (Cameron et al, 1989a, 1986b), and found to produce an overall flow field and combustor performance that is representative of a gas turbine can combustor
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