Mixing of Multiple Jets in a Can Combustor

Ebbinghaus, Alexandra; Swithenbank, J.

doi:10.1115/95-gt-257

Cited by 2 publications

(1 citation statement)

References 3 publications

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“…In particular, two exit profiles were desired including an inboard peaked profile and a uniform exit temperature profile. The inboard Through the use of an existing can combustor configuration, Ebbinghaus and Swithenbank (1995) were able to determine the effects of varying the number of primary, secondary, and dilution jets at each axial location throughout the simulator (refer to In an effort to develop an aero-engine for the 100-seat aircraft market, Pratt and Whitney used computational fluid dynamics to design and construct a full annular test rig. A Lagrangian fuel spray model along with a combustion model were only two of the major components included in the CFD simulations presented in the first part of this paper by Malecki et al (2001).…”

Section: Reacting Combustor Experimental Studies and Computational Simentioning

confidence: 99%

Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aero-Engine

Vakil

Thole

2003

Volume 2: Turbo Expo 2003

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The highly competitive gas turbine industry has been motivated by consumer demands for higher power-to-weight ratios, increased thermal efficiencies, and reliability while maintaining affordability. In its continual quest, the industry must continually try to raise the turbine inlet temperature, which according to the well-known Brayton cycle is key to higher engine efficiencies. The desire for increased turbine inlet temperatures creates an extremely harsh environment for the combustor liner in addition to the components downstream of the combustor. Shear layers between the dilution jets and the mainstream, as well as combustor liner film-cooling interactions create a complex mean flow field within the combustor, which is not easy to model. A completely uniform temperature and velocity profile at the combustor exit is desirable from the standpoint of reducing the secondary flows in the turbine. However, this seldom occurs due to a lack of thorough mixing within the combustor. Poor mixing results in non-uniformities, such as hot streaks, and allow non-combusted fuel to exit the combustor.This investigation developed a database documenting the thermal and flow characteristics within a combustor simulator representative of the flowfield within a gas turbine aero-engine. Three-and two-component laser Doppler velocimeter measurements were completed to quantify the flow and turbulence fields, while a thermocouple rake was used to quantify the thermal fields.The measured results show very high turbulence levels due to the dilution flow injection. Directly downstream of the dilution jets, an increased thickness in the filmcooling was noted with a fairly non-homogeneous temperature field across the combustor width. A highly turbulent shear layer was found at the leading edge of the dilution jets. Measurements also showed that a relatively extensive recirculation region existed downstream of the dilution jets. Despite the lack of film-cooling injection at the trailing edge of the dilution hole, there existed coolant flow indicative of a horse-shoe vortex wrapping around the jet. As a result of the dilution jet interaction with the mainstream flow, kidney-shaped thermal fields and counter-rotating vortices developed. These vortices serve to enhance combustor mixing.iii

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Section: Reacting Combustor Experimental Studies and Computational Simentioning

confidence: 99%