Accession Number : AD1032042


Title :   Flow Field Dynamics in a High-g Ultra-Compact Combustor


Descriptive Note : Technical Report,01 Sep 2013,22 Dec 2016


Corporate Author : AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH WRIGHT-PATTERSON AFB United States


Personal Author(s) : Cottle,Andrew E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/1032042.pdf


Report Date : 01 Dec 2016


Pagination or Media Count : 423


Abstract : The Ultra Compact Combustor (UCC) presents a novel solution to the advancement of aircraft gas turbine engine performance. A high-g UCC design operates by diverting a portion of the axial compressor flow into a circumferential combustion cavity positioned about the engine outer diameter. The circumferential cavity (CC) provides the necessary residence length and time for combustion within reduced axial lengths; furthermore, high rates of centrifugal acceleration termed high-g loading are imposed upon the swirling cavity flow. These high-g conditions are hypothesized to increase flame speed, reduce flame length, and improve lean blow-out performance. Work at AFIT was sponsored by the Air Force Office of Scientific Research to study high-g combustion. This research capitalized on the availability of advanced flow diagnostic data coupled with a computational fluid dynamics (CFD) model to provide detailed insight into the high-g flow field and combustion dynamics. Results indicated that combustion could be sustained and controlled in a manner suitable for integration into modern gas turbine engine architecture.


Descriptors :   COMBUSTORS , computational fluid dynamics , turbulent mixing , secondary flow , burning rate , dielectric gases , pressure measurement , laser induced fluorescence , flow visualization , hydrodynamics , boundary layer , heat transfer , chemical reactions , particle image velocimetry , laser spectroscopy , GAS TURBINES


Subject Categories : Fluid Mechanics
      Combustion and Ignition


Distribution Statement : APPROVED FOR PUBLIC RELEASE