Accession Number : ADA627333


Title :   Measured Heat Transfer in a Transonic Fan Rig at Casing with Implications on Performance


Descriptive Note : Conference paper


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA


Personal Author(s) : Turner, Mark G ; Nemnem, Ahmed ; Gannon, Anthony ; Hobson, Garth ; Sanz, Wolfgang


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a627333.pdf


Report Date : 15 Jun 2015


Pagination or Media Count : 10


Abstract : A highly loaded transonic fan with a splittered rotor and maximum pressure ratio of 2 has been tested at the Naval Postgraduate School. Temperatures on the casing outer wall have been measured using thermocouples in order to assess the heat transfer. An axisymmetric heat transfer analysis has shown that the heat transfer downstream of the rotor through the casing leads to a overstatement of the experimental efficiency by 0.57% and 0.51% for 100% and 90% speed respectively. Just above the rotor is an abradable material that can be considered adiabatic. This heat escapes only aft of the rotor and upstream of the total pressure and total temperature probes. For rotors without an adiabatic casing, the effect would be considerably higher. In addition, heat transfer coefficients have been determined that can be used to assess other compressor applications.


Descriptors :   *COMPRESSOR ROTORS , *HEAT TRANSFER COEFFICIENTS , *PERFORMANCE(ENGINEERING) , *TRANSONIC CHARACTERISTICS , ADIABATIC CONDITIONS , BLADE TIPS , COMPUTATIONAL FLUID DYNAMICS , CONVECTION(HEAT TRANSFER) , DOWNSTREAM FLOW , FAN BLADES , HIGH VELOCITY , MECHANICAL PROPERTIES , SCHEMATIC DIAGRAMS , STATORS , TEST AND EVALUATION , THERMOCOUPLES , TURBOMACHINERY , TURBULENT FLOW


Subject Categories : Hydraulic and Pneumatic Equipment
      Fluid Mechanics
      Thermodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE