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Numerical Evaluation of an Ejector-Enhanced Resonant Pulse Combustor with a Poppet Inlet Valve and a Converging Exhaust NozzleA computational investigation of a pressure-gain combustor system for gas turbine applications is presented. The system consists of a valved pulse combustor and an ejector, housed within a shroud. The study focuses on two enhancements to previous models, related to the valve and ejector components. First, a new poppet inlet valve system is investigated, replacing the previously used reed valve configuration. Secondly, a new computational approach to approximating the effects of choked turbine inlet guide vanes present immediately downstream of the Ejector-Enhanced Resonant Pulse Combustor (EERPC) is investigated. Instead of specifying a back pressure at the EERPC exit boundary (as was done in previous studies) the new model adds a converging-diverging (CD) nozzle at the exit of the EERPC. The throat area of the CD nozzle can be adjusted to obtain the desired back pressure level and total mass flow rate. The results presented indicate that the new poppet valve configuration performs nearly as well as the original reed valve system, and that the addition of the CD nozzle is an effective method to approximate the exit boundary effects of a turbine present downstream of the EERPC. Furthermore, it is shown that the more acoustically reflective boundary imposed by a nozzle as compared to a constant pressure surface does not significantly affect operation or performance.
Document ID
20170000959
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Yungster, Shaye
(Ohio Aerospace Inst. Brook Park, OH, United States)
Paxson, Daniel E.
(NASA Glenn Research Center Cleveland, OH United States)
Perkins, Hugh D.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
January 31, 2017
Publication Date
July 25, 2016
Subject Category
Fluid Mechanics And Thermodynamics
Aeronautics (General)
Report/Patent Number
GRC-E-DAA-TN33417
Meeting Information
Meeting: AIAA/SAE/ASEE Joint Propulsion Conference
Location: Salt Lake City, UT
Country: United States
Start Date: July 25, 2016
End Date: July 27, 2016
Sponsors: Society of Automotive Engineers, Inc., American Society for Electrical Engineers, American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNC13BA10B
WBS: WBS 109492.02.03.02.30
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Computational Fluid Dynamics (CFD
Pressure Gain Combustion
Pulsejet
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