Numerical Investigation of Shrouded Ejector-Enhanced Pulse Combustor Performance at High Pressure
Author:
Affiliation:
1. Ohio Aerospace Institute, Cleveland, Ohio 44142
2. NASA Glenn Research Center, 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.B36082
Reference41 articles.
1. LefebvreA. H., Gas Turbine Combustion, 2nd ed., Taylor and Francis, Philadelphia, PA, 1999, pp. 101–104, Chap. 4.
2. PaxsonD. E.DoughertyK. T. “Ejector Enhanced Pulsejet Based Pressure Gain Combustors: An Old Idea with a New Twist,” AIAA Paper 2005-4216, July 2005.
3. Aerothermodynamics of Gas Turbine and Rocket Propulsion
4. CatchpoleB. G.RunacresA. “Constant Volume Gas Turbine Experiments with Gaseous Fuel in a Rotating Pocket Combustor,” Australian Defense Scientific Service Aeronautical Research Lab., Mechanical Engineering Note 353, Melbourne, Australia, Oct. 1974.
5. Small gas turbine using a second-generation pulse combustor
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