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Characterization of Swirl-Venturi Lean Direct Injection Designs for Aviation Gas-Turbine CombustionInjector geometry, physical mixing, chemical processes, and engine cycle conditions together govern performance, operability and emission characteristics of aviation gas-turbine combustion systems. The present investigation explores swirl-venturi lean direct injection combustor fundamentals, characterizing the influence of key geometric injector parameters on reacting flow physics and emission production trends. In this computational study, a design space exploration was performed using a parameterized swirl-venturi lean direct injector model. From the parametric geometry, 20 three-element lean direct injection combustor sectors were produced and simulated using steady-state, Reynolds-averaged Navier-Stokes reacting computations. Species concentrations were solved directly using a reduced 18-step reaction mechanism for Jet-A. Turbulence closure was obtained using a nonlinear κ-ε model. Results demonstrate sensitivities of the geometric perturbations on axially averaged flow field responses. Output variables include axial velocity, turbulent kinetic energy, static temperature, fuel patternation and minor species mass fractions. Significant trends have been reduced to surrogate model approximations, intended to guide future injector design trade studies and advance aviation gas-turbine combustion research.
Document ID
20170000472
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Heath, Christopher M.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
January 18, 2017
Publication Date
July 14, 2013
Subject Category
Fluid Mechanics And Thermodynamics
Aircraft Propulsion And Power
Report/Patent Number
GRC-E-DAA-TN31842
Meeting Information
Meeting: AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Location: San Jose, CA
Country: United States
Start Date: July 14, 2013
End Date: July 17, 2013
Sponsors: Society of Automotive Engineers, Inc., American Inst. of Aeronautics and Astronautics, American Society of Mechanical Engineers, American Society for Electrical Engineers
Funding Number(s)
WBS: WBS 110076.02.03.04.10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Combustion Chamber
Computational Fluid Dynamics
Simulation
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