Characterization of Swirl-Venturi Lean Direct Injection Designs for Aviation Gas Turbine Combustion-Reference-Cited by-同舟云学术

Characterization of Swirl-Venturi Lean Direct Injection Designs for Aviation Gas Turbine Combustion

Published:2014-09 Issue:5 Volume:30 Page:1334-1356
ISSN:0748-4658
Container-title:Journal of Propulsion and Power
language:en
Short-container-title:Journal of Propulsion and Power

Author:

Heath Christopher M.¹

Affiliation:

1. Analysis and Optimization Branch, NASA John H. Glenn Research Center at Lewis Field, Cleveland, Ohio 44135

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.B35077

Reference27 articles.

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2. TacinaR.LeeP.WeyC. “A Lean-Direct-Injection Combustor Using a 9 Point Swirl-Venturi Fuel Injector,” ISABE Paper 2005-1106, 2005.

3. Sector Tests of a Low NOx, Lean-Direct-Injection, Multipoint Integrated Module Combustor Concept

4. FuY. “Aerodynamics and Combustion of Axial Swirlers,” Ph.D. Dissertation, Dept. of Aerospace Engineering and Engineering Mechanics, Univ. of Cincinnati, Cincinnati, OH, 2008.

5. HicksY. R.HeathC. M.AndersonR. C.TacinaK. M. “Investigations of a Combustor Using a 9-Point Swirl-Venturi Fuel Injector: Recent Experimental Results,” ISABE Paper 2011-1106, 2011.

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