Accession Number : ADA586167


Title :   Pressure Gain Combustion for Gas Turbines


Descriptive Note : Final rept. 20 Sep 2010-19 Jan 2013


Corporate Author : CAMBRIDGE UNIV (UNITED KINGDOM)


Personal Author(s) : Miller, Robert J ; Heffer, J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a586167.pdf


Report Date : 20 Aug 2013


Pagination or Media Count : 24


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.


Descriptors :   *COMBUSTION , *GAS TURBINES , COMPUTATIONAL FLUID DYNAMICS , EFFICIENCY , EJECTORS , GAIN , GEOMETRY , NOZZLES , PERFORMANCE(ENGINEERING) , PRESSURE , TURBOMACHINERY , VALVES


Subject Categories : Combustion and Ignition
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE