Abstract
Parts I and II of this paper report the measurement and analysis of detailed heat flux distributions obtained on the nozzle guide vane (NGV), rotor, and shroud of the full-stage rotating turbine of the Garrett TFE 731-2 engine. Part I is devoted to a description of the experimental apparatus and the data analysis procedure. Part II is concerned with the experimental results and their comparison with predictions obtained using a flat-plate technique and with predictions obtained using STAN5. Measurements were performed for values of the ratio of wall temperature to total temperature equal to 0.21, 0.33, and 0.53. For the NGV airfoil and rotor blade, the influence of wall temperature ratio on the Stanton number is shown to be generally 10 percent or less. For the NGV airfoil, and the rotor blade pressure surface, the flat-plate turbulent-flow prediction provides a reasonably good comparison with the data. With the rotor operating, the state of the boundary layer generally appears to be turbulent for both the NGV airfoil and the rotor blade. Predictions obtained using STAN5 confirm that boundary layer transition occurs at a value of Reθ substantially less than 200.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
