Research Papers

Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part I: Experimental Approach

[+] Author and Article Information
C. W. Haldeman, R. M. Mathison, M. G. Dunn, S. A. Southworth, J. W. Harral

Gas Turbine Laboratory,  The Ohio State University, Columbus, OH 43235

G. Heitland

 Honeywell Aerospace, Phoenix, AZ 85034

J. Turbomach 130(2), 021015 (Mar 24, 2008) (10 pages) doi:10.1115/1.2750676 History: Received July 13, 2006; Revised July 16, 2006; Published March 24, 2008

This paper describes the experimental approach utilized to perform experiments using a fully cooled rotating turbine stage to obtain film effectiveness measurements. Significant changes to the previous experimental apparatus were implemented to meet the experimental objectives. The modifications include the development of a synchronized blowdown facility to provide cooling gas to the turbine stage, installation of a heat exchanger capable of generating a uniform or patterned inlet temperature profile, novel utilization of temperature and pressure instrumentation, and development of robust double-sided heat flux gauges. With these modifications, time-averaged and time-accurate measurements of temperature, pressure, surface heat flux, and film effectiveness can be made over a wide range of operational parameters, duplicating the nondimensional parameters necessary to simulate engine conditions. Data from low Reynolds number experiments are presented to demonstrate that all appropriate scaling parameters can be satisfied and that the new components have operated correctly. Along with airfoil surface heat transfer and pressure data, temperature and pressure data from inside the coolant plenums of the vane and rotating blade airfoils are presented. Pressure measurements obtained inside the vane and blade plenum chambers illustrate passing of the wakes and shocks as a result of vane/blade interaction. Part II of this paper (Haldeman, C. W., Mathison, R. M., Dunn, M. G., Southworth, S. A., Harral, J. W., and Heltland, G., 2008, ASME J. Turbomach., 130(2), p. 021016) presents data from the low Reynolds number cooling experiments and compares these measurements to CFD predictions generated using the Numeca FINE/Turbo package at multiple spans on the vanes and blades.

Copyright © 2008 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Figure 7

Large cooling facility

Grahic Jump Location
Figure 8

Schematic of cooling connections

Grahic Jump Location
Figure 10

Overall matrix temperature

Grahic Jump Location
Figure 11

Cooling experiment time history

Grahic Jump Location
Figure 12

Corrected speed variation

Grahic Jump Location
Figure 13

Overall stage pressures and pressure ratio

Grahic Jump Location
Figure 14

Rake temperatures at design point

Grahic Jump Location
Figure 15

Cooling gas internal pressures

Grahic Jump Location
Figure 16

Internal temperatures

Grahic Jump Location
Figure 17

Normalized rotor pressures

Grahic Jump Location
Figure 18

Power spectrum of internal rotor pressures

Grahic Jump Location
Figure 1

Honeywell turbine in TTF

Grahic Jump Location
Figure 3

Turbine cooling paths

Grahic Jump Location
Figure 4

Vane cooling hole pattern

Grahic Jump Location
Figure 5

Blade cooling holes

Grahic Jump Location
Figure 6

Blade suction side, 50% span instruments




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In