Accession Number : ADA608852


Title :   Convective Heat Transfer with and without Film Cooling in High Temperature, Fuel Rich and Lean Environments


Descriptive Note : Doctoral thesis


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


Personal Author(s) : Greiner, Nathan J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a608852.pdf


Report Date : Sep 2014


Pagination or Media Count : 432


Abstract : Modern turbine engines require high turbine inlet temperatures and pressures to maximize thermal efficiency. Increasing the turbine inlet temperature drives higher heat loads on the turbine surfaces. In addition, increasing pressure ratio increases the turbine coolant temperature such that the ability to remove heat decreases. As a result, highly effective external film cooling is required to reduce the heat transfer to turbine surfaces. Testing of film cooling on engine hardware at engine temperatures and pressures can be exceedingly difficult and expensive. Thus, modern studies of film cooling are often performed at near ambient conditions. However, these studies are missing an important aspect in their characterization of film cooling effectiveness. Namely, they do not model effect of thermal property variations that occur within the boundary and lm cooling layers at real engine conditions. Also, turbine surfaces can experience significant radiative heat transfer that is not trivial to estimate analytically.


Descriptors :   *FILM COOLING , *HEAT TRANSFER , CONVECTION(HEAT TRANSFER) , COOLANTS , COOLING , ENGINES , ENVIRONMENTS , FUELS , HEAT , HIGH TEMPERATURE , INLETS , LAYERS , MODELS , PRESSURE , RADIATIVE TRANSFER , RATIOS , SKILLS , SURFACES , TEMPERATURE , THERMAL PROPERTIES , THESES , TURBINES


Subject Categories : Thermodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE