Research Papers

Direct Numerical Simulations of a High-Pressure Turbine Vane

[+] Author and Article Information
Andrew P. S. Wheeler

Whittle Laboratory,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: a.wheeler@eng.cam.ac.uk

Richard D. Sandberg, Neil D. Sandham, Richard Pichler

Engineering and the Environment,
University of Southampton,
Southampton So17 1BJ, UK

Vittorio Michelassi

GE Global Research,
Munich D-85748, Germany

Greg Laskowski

GE Aviation,
Lynn, MA 01905

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 21, 2015; final manuscript received December 18, 2015; published online February 17, 2016. Editor: Kenneth C. Hall.

J. Turbomach 138(7), 071003 (Feb 17, 2016) (9 pages) Paper No: TURBO-15-1231; doi: 10.1115/1.4032435 History: Received October 21, 2015; Revised December 18, 2015

In this paper, we establish a benchmark data set of a generic high-pressure (HP) turbine vane generated by direct numerical simulation (DNS) to resolve fully the flow. The test conditions for this case are a Reynolds number of 0.57 × 106 and an exit Mach number of 0.9, which is representative of a modern transonic HP turbine vane. In this study, we first compare the simulation results with previously published experimental data. We then investigate how turbulence affects the surface flow physics and heat transfer. An analysis of the development of loss through the vane passage is also performed. The results indicate that freestream turbulence tends to induce streaks within the near-wall flow, which augment the surface heat transfer. Turbulent breakdown is observed over the late suction surface, and this occurs via the growth of two-dimensional Kelvin–Helmholtz spanwise roll-ups, which then develop into lambda vortices creating large local peaks in the surface heat transfer. Turbulent dissipation is found to significantly increase losses within the trailing-edge region of the vane.

Copyright © 2016 by ASME
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Fig. 4

Mesh block structure and mesh details at the leading and trailing-edges. Every fourth grid line is shown (mesh A).

Grahic Jump Location
Fig. 3

Power spectral density of total velocity upstream of the vane leading-edge (x=−0.3, y = 0.0) and within the wake (x = 1.017, y=−1.49)

Grahic Jump Location
Fig. 2

Snapshot of isosurface of Q-criterion = 25 with inlet freestream turbulence Tu=3.5%. Isosurface colored with spanwise velocity w normalized by the inlet velocity (block 2 shown).

Grahic Jump Location
Fig. 1

Surface curvature of vane determined from published manufacturing coordinates of Ref. [1] and the corrected profile used in this study

Grahic Jump Location
Fig. 5

Spanwise mode amplitudes (mesh A)

Grahic Jump Location
Fig. 6

Sensitivity of wall shear stress to mesh density

Grahic Jump Location
Fig. 7

Near-wall grid size measured in wall units (mesh A)

Grahic Jump Location
Fig. 8

Boundary layer time-average velocity profiles, 125 grid points shown (mesh A)

Grahic Jump Location
Fig. 9

Ratio of in-plane cell size to Kolmogorov length-scale computed from time-average turbulent dissipation for mesh A

Grahic Jump Location
Fig. 10

Isentropic Mach number distribution and comparison with experimental data of Arts et al. [1]

Grahic Jump Location
Fig. 11

Comparison of time-average loss and exit angle with experimental data of Arts et al. [1] determined at 40%Cax axial chord downstream of the trailing-edge

Grahic Jump Location
Fig. 20

Rise in irreversible entropy through the vane passage and downstream

Grahic Jump Location
Fig. 17

Power spectral density at two near-wall monitor points (y+≈1) and a monitor point within the wake

Grahic Jump Location
Fig. 18

Instantaneous snapshot showing contours of gas temperature at the first grid point away from the wall

Grahic Jump Location
Fig. 19

Isosurfaces of Q-criterion = 25 colored by spanwise velocity near the leading-edge

Grahic Jump Location
Fig. 13

Two instantaneous snapshots (Δt=0.12) showing contours of density gradient magnitude (gray scale) and gas temperature at the first grid point away from the wall (color scale). Marked on the figure are: (a) upstream moving pressure waves, (b) development of 2d spanwise instabilities over the aft suction surface, (c) fluctuations in surface heat flux due to pressure wave reflections, and (d) near-wall streaks

Grahic Jump Location
Fig. 12

Comparison of predicted heat flux with experimental data of Arts et al. [1]

Grahic Jump Location
Fig. 14

Space–time diagrams of surface shear, heat flux and pressure from monitor points over the aft suction surface. The surface distance is measured from the leading-edge, and normalized by axial chord.

Grahic Jump Location
Fig. 15

Isosurfaces of Q-criterion = 50 colored by spanwise velocity in the region of transition

Grahic Jump Location
Fig. 16

Isosurfaces of vorticity magnitude = 1000 colored by density within transition region




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