0
Research Papers

A New Alternative for Reduction in Secondary Flows in Low Pressure Turbines

[+] Author and Article Information
Diego Torre

 Industria de Turbo Propulsores S.A. (ITP), Madrid 28830, Spaindiego.torre@itp.es

Raúl Vázquez

Head of Aerodynamics and Systems, Industria de Turbo Propulsores S.A. (ITP), Madrid 28830, Spainraul.vazquez@itp.es

Elena de la Rosa Blanco

Department of Engineering, Cambridge University, Cambridge CB3 0DY, UK

Howard P. Hodson

Department of Engineering, Whittle Laboratory, Cambridge University, Cambridge CB3 0DY, UK

J. Turbomach 133(1), 011029 (Sep 28, 2010) (10 pages) doi:10.1115/1.4001365 History: Received October 23, 2007; Revised December 23, 2009; Published September 28, 2010; Online September 28, 2010

This paper describes a new flow mechanism for the reduction in secondary flows in low pressure turbines using the benefit of contoured endwalls. The extensive application of contoured endwalls in recent years has provided a deeper understanding of the physical phenomenon that governs the reduction in secondary flows. Based on this understanding, the endwall geometry of a linear cascade of solid-thin profiles typical of low pressure turbines has been redesigned. Experimental data are presented for the validation of this new solution. Based on these data, a reduction of 72% in the secondary kinetic energy helicity (SKEH) and 20% in the mixed-out endwall losses can be obtained. Computational fluid dynamics simulations are also presented to illustrate the effect of the new endwall on the secondary flows. Furthermore, an explanation of the flow mechanism that governs the reduction in the SKEH, and the losses is given.

Copyright © 2011 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Endwall height deviations (contours in mm)

Grahic Jump Location
Figure 2

Measured pitchwise mass averaged gross stagnation pressure loss coefficient

Grahic Jump Location
Figure 3

Measured pitchwise mass averaged deviation angle

Grahic Jump Location
Figure 4

Measured pitchwise mass averaged SKEH

Grahic Jump Location
Figure 5

Experimental contours: planar cascade

Grahic Jump Location
Figure 6

Experimental contours: contoured cascade

Grahic Jump Location
Figure 7

Endwall flow visualization

Grahic Jump Location
Figure 8

Measured and calculated pitchwise mass averaged gross stagnation pressure loss coefficient

Grahic Jump Location
Figure 9

Measured and calculated pitchwise mass averaged deviation angles

Grahic Jump Location
Figure 10

Measured and calculated pitchwise mass averaged SKEHs

Grahic Jump Location
Figure 11

Calculated particle traces on the endwall

Grahic Jump Location
Figure 12

Calculated loss and helicity contours at −20% Cax: planar (left) and contoured (right) cascades

Grahic Jump Location
Figure 13

Calculated loss and helicity contours at 5% Cax: planar (left) and contoured (right) cascades

Grahic Jump Location
Figure 14

Calculated loss and helicity contours at 30% Cax: planar (left) and contoured (right) cascades

Grahic Jump Location
Figure 15

Calculated loss and helicity contours at 60% Cax: planar (left) and contoured (right) cascades

Grahic Jump Location
Figure 16

Calculated loss and helicity contours at 90% Cax: planar (left) and contoured (right) cascades

Grahic Jump Location
Figure 17

Suction side wall shear stresses

Grahic Jump Location
Figure 18

Calculated loss and helicity contours at 120% Cax: planar (left) and contoured (right) cascades

Grahic Jump Location
Figure 19

Calculated loss and streamwise vorticity contours at 150% Cax

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