Accession Number : ADA558282


Title :   Cooling Requirements for the Ultra-Compact Combustor


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT


Personal Author(s) : Johnson, Donald D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a558282.pdf


Report Date : Mar 2012


Pagination or Media Count : 148


Abstract : Over the past several years, AFIT and the Air Force Research Laboratory have collaboratively investigated a novel combustor system that is compact in design and has potential use in an inter-turbine burner system. The ultra-compact combustor (UCC) design wraps the combustion section circumferentially around the axial core flow and exploits the use of high-g combustion. The combustor's volume and weight are reduced by integrating the exit compressor vane and the turbine inlet vane. This creates a new hybrid vane that resides directly below the circumferential combustor. Recently, a computational effort to understand the fundamental aspects of the UCC on a fighter scale model revealed that high temperatures are likely to occur on the hybrid vane. To address this issue, film-cooling is being explored for the UCC in a computational manner. Simulations of normal coolant hole, contoured trench, and hybrid normal and contoured trench configurations were performed for blowing ratios of M=1, 1.5 and 2. Secondary reactions formed due to the oxygen-rich coolant air reacting with unburned fuel as it exited the circumferential cavity. Although secondary reactions occurred, a decrease in unburned radicals was noticed at the exit of the UCC due to enhanced completion of reactions upstream.


Descriptors :   *COMBUSTORS , *FILM COOLING , *FLUID MECHANICS , *GAS TURBINES , *HIGH TEMPERATURE , *JET ENGINES , CENTRIFUGAL FORCE , CHEMICAL REACTIONS , COMBUSTION , COMPRESSOR COMPONENTS , COMPUTERIZED SIMULATION , GRIDS , HYBRID SYSTEMS , INLET GUIDE VANES , NUMERICAL ANALYSIS , THESES , TURBULENCE


Subject Categories : Fluid Mechanics
      Thermodynamics
      Combustion and Ignition
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE