A Numerical Study of Secondary Flow in Axial Turbines With Application to Radial Transport of Hot Streaks

[+] Author and Article Information
Dilip Prasad

United Technologies Research Center, East Hartford, CT 06108

Gavin J. Hendricks

Pratt & Whitney, East Hartford, CT 06108

J. Turbomach 122(4), 667-673 (Feb 01, 2000) (7 pages) doi:10.1115/1.1313817 History: Received February 01, 2000
Copyright © 2000 by ASME
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
(a) Illustration of vane exit geometry and nomenclature; (b) view of the vane trailing edge looking upstream; solid line represents the trailing edge
Grahic Jump Location
Schematic illustration of the secondary flow in the rotor passage. The direction of the primary flow is out of the plane. Note that in the upper part of the blade passage, the radial velocity contribution from the secondary flow (solid line) reinforces that from the relative eddy (broken line) near the pressure surface.
Grahic Jump Location
Variation of the vane exit flow angle at midpassage as a function of span. The solid line illustrates the vane exit flow angle for the baseline geometry, while ––– and ⋅–⋅ represent positive and reverse twist (see “Secondary Flow Control”), respectively.
Grahic Jump Location
Contours of total temperature at the inlet boundary; values range from 1.05 to 1.3 in steps of 0.05
Grahic Jump Location
Spanwise variation of pitch angle at three circumferential locations. The solid lines represent the results of the steady run, while the broken lines represent those for the time-averaged unsteady run.
Grahic Jump Location
Temperature distribution in blade at 33 percent chord: (a) steady computation, (b) time-averaged unsteady computation. The segregation of the hot fluid toward pressure surface (on the right side) is evident.
Grahic Jump Location
Velocity triangle at vane exit
Grahic Jump Location
Illustration of (a) positive, (b) nominal, and (c) reverse twist
Grahic Jump Location
Steady-state temperature distribution close to the pressure surface of the blade passage for vanes with: (a) positive twist, (b) nominal twist, and (c) reverse twist
Grahic Jump Location
Pitch angle at a streamwise distance of 0.33 chord downstream of the leading edge of the rotor blade, along a radial line close to the pressure surface; the nominal case is represented by –⋅⋅–, while ––– and — represent the positive and reverse twist cases, respectively
Grahic Jump Location
Instantaneous view of temperature contours in four successive blade passages for vanes with: (a) positive twist, and (b) reverse twist




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