Accession Number : ADA482412


Title :   Heat Transfer Measurements for a Film Cooled Turbine Vane Cascade


Corporate Author : ARMY RESEARCH LAB CLEVELAND OH VEHICLE TECHNOLOGY DIRECTORATE


Personal Author(s) : Thurman, Douglas R ; Poinsatte, Philip E ; Heidmann, James D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a482412.pdf


Report Date : May 2008


Pagination or Media Count : 26


Abstract : Experimental heat transfer and pressure measurements were obtained on a large scale film cooled turbine vane cascade. The objective was to investigate heat transfer on a commercial high pressure first stage turbine vane at near engine Mach and Reynolds number conditions. Additionally blowing ratios and coolant density were also matched. Numerical computations were made with the Glenn-HT code of the same geometry and compared with the experimental results. We used a transient thermochromic liquid crystal technique to obtain steady state heat transfer data on the mid-span geometry of an instrumented vane with 12 rows of circular and shaped film cooling holes. A mixture of SF6 and Argon gases was used for film coolant to match the coolant-to-gas density ratio of a real engine. The exit Mach number and Reynolds number were 0.725 and 2.7 million respectively. Trends from the experimental heat transfer data matched well with the computational prediction, particularly for the film cooled case.


Descriptors :   *HEAT TRANSFER , *TURBINES , *FILM COOLING , LIQUID CRYSTALS , THERMOCHROMIC MATERIALS , MACH NUMBER , REYNOLDS NUMBER , PRESSURE MEASUREMENT , STEADY STATE


Subject Categories : Thermodynamics
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE