Pressure Gain Combustion for Gas Turbines

Abstract

This final technical report consists of two interim progress report received from the grantee in Nov. 2011 and Sept. 2013. Pressure gain combustion has the potential to increase gas turbine efficiency by more than 10%. There is gap in the technology necessary for such improvements. Namely, conventional turbines do not work efficiently in the unsteady flow produced by pressure gain combustors. This effort was to examine the problem using simplified experiments and numerical simulations to reveal the fundamental fluid mechanics of these unsteady flows. Specifically investigated were the effects of the geometry, jet Mach number, frequency, and temperature.

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Document Details

Document Type
Technical Report
Publication Date
Aug 20, 2013
Accession Number
ADA586167

Entities

People

  • J. Heffer
  • Robert J Miller

Organizations

  • University of Cambridge

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Combustion
  • Combustors
  • Computational Fluid Dynamics
  • Engines
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Frequency
  • Gas Turbines
  • Geometry
  • Heat Engines
  • Mach Number
  • Pressure Gain Combustion
  • Turbines
  • Turbomachinery
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion science or combustion engineering.
  • Defense Acquisition Program Management