0
Research Papers

Aerodynamic Performance of a Very High Lift Low Pressure Turbine Airfoil (T106C) at Low Reynolds and High Mach Number With Effect of Free Stream Turbulence Intensity

[+] Author and Article Information
Jan Michálek1

Turbomachinery and Propulsion Department, “Jacques Chauvin” Laboratory,  von Karman Institute for Fluid Dynamics, 1640 Rhode-Saint-Genèse, Belgiummichalek@vki.ac.be

Michelangelo Monaldi

Turbomachinery and Propulsion Department, “Jacques Chauvin” Laboratory,  von Karman Institute for Fluid Dynamics, 1640 Rhode-Saint-Genèse, Belgiummonaldi@vki.ac.be

Tony Arts

Turbomachinery and Propulsion Department, “Jacques Chauvin” Laboratory,  von Karman Institute for Fluid Dynamics, 1640 Rhode-Saint-Genèse, Belgiumarts@vki.ac.be

1

Corresponding author.

J. Turbomach 134(6), 061009 (Aug 27, 2012) (10 pages) doi:10.1115/1.4006291 History: Received April 04, 2011; Revised June 21, 2011; Published August 27, 2012; Online August 27, 2012

A detailed experimental analysis of the effects of the Reynolds number and free-stream turbulence intensity on the aerodynamic performance of a very high-lift, mid-loaded low-pressure turbine blade (T106C) is presented in this paper. The study was carried out on a large scale linear cascade in the VKI S1/C high-speed wind tunnel, operating at high exit Mach number (0.65) with a range of low Reynolds numbers (80,000–160,000) and three levels of free-stream turbulence intensity (0.8–3.2%). In the first part of the paper, the overall aerodynamic performance of the airfoil is presented, based on mid-span measurements performed by means of static pressure taps, hot-film sensors and a five-hole probe traversing downstream of the cascade. Some specific features of separated flow transition are also discussed for selected cases. The second part presents the analysis of the results in terms of correlations derived for the characteristic points of boundary layer separation and transition. A comparison with some previously published prediction models is shown. The large variety of boundary conditions provides a unique database for validating codes dealing with separated flow transition in turbomachinery.

FIGURES IN THIS ARTICLE
<>
Copyright © 2012 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

The S-1/C high speed, variable density wind tunnel

Grahic Jump Location
Figure 2

Selected isentropic Mach number distributions along the suction side of the T106c airfoil for three different Re2,is ; No Grid

Grahic Jump Location
Figure 3

Mass-weighted kinetic energy losses for three FSTI as a function of Re2,is

Grahic Jump Location
Figure 4

Mean exit flow angle reduction for three FSTI as a function of Re2,is

Grahic Jump Location
Figure 5

Evolution of the wall-shear stress, the rms and the intermittency factor along the suction side at Re2,is  = 160,000 and for No Grid (S = separation, R = reattachment, t = onset of transition; T = end of transition)

Grahic Jump Location
Figure 6

Power density spectra and time traces of the hot-films sensors at selected points along the suction side; Re2,is  = 160,000, No Grid

Grahic Jump Location
Figure 7

Evolution of the wall-shear stress, the rms and the intermittency factor along the suction side at Re2,is  = 100,000 and No Grid (S = separation, R1 = 1st reattachment-like point, t = onset of transition; T = end of transition)

Grahic Jump Location
Figure 8

Power density spectra and time traces of the hot-films sensors at selected points along the suction side; Re2,is  = 100,000, No Grid

Grahic Jump Location
Figure 9

Isentropic Mach number distributions along the suction side of the T106c airfoil for three different turbulence intensities; Re2,is  = 100,000

Grahic Jump Location
Figure 10

Evolution of the wall-shear stress, the rms and the intermittency factor evolution along the suction side at Re2,is  = 100,000 and Grid 5 (S = separation p., R = reattachment p., t = onset of transition; T = end of transition)

Grahic Jump Location
Figure 11

Local Reynolds number at separation as function of the acceleration parameter and turbulence intensity

Grahic Jump Location
Figure 12

Local Reynolds number at the pressure recovery point as a function of Reynolds number at the separation and turbulence intensity

Grahic Jump Location
Figure 13

Local Reynolds number at the reattachment as a function of Reynolds number at the separation and turbulence intensity

Grahic Jump Location
Figure 14

Local Reynolds number at the onset of transition as a function of Reynolds number at the separation

Tables

Errata

Discussions

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