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The Effect of Mach Number on the Loss Generation of LP Turbines

[+] Author Affiliations
Raúl Vázquez

ITP - Industria de Turbopropulsores S.A., Madrid, SpainUPM - Universidad Politécnica Madrid, Madrid, Spain

Diego Torre

ITP - Industria de Turbopropulsores S.A., Madrid, Spain

Paper No. GT2012-68555, pp. 1131-1142; 12 pages
doi:10.1115/GT2012-68555
From:
  • ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
  • Volume 8: Turbomachinery, Parts A, B, and C
  • Copenhagen, Denmark, June 11–15, 2012
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4474-8
  • Copyright © 2012 by ASME

abstract

The effect of Mach number on the loss generation of Low Pressure (LP) Turbines has been investigated experimentally in a pair of turbine high-speed rigs. Both rigs consist of a rotor-stator configuration. All the airfoils are high lift, high aspect ratio and high turning blades that are characteristic of state of the art LP Turbines.

Both rigs are identical with exception of the stator. Two sets of stators have been manufactured and tested. The aerodynamic shape of both stators have been designed in order to achieve the same spanwise distribution of Cp (Compressible Pressure coefficient) over the airfoil surface, each one to its corresponding design Mach number (0.61 and 0.88 respectively).

The aim of this experiment is to obtain the sensitivity of profile and endwall losses to Mach number by means of a back-to-back comparison between both sets of airfoils. Because the two sets of stators maintain the same pressure coefficient distribution, Reynolds number and velocity triangles, each one to its corresponding design Mach number; one can state that the results are only affected by the compressibility.

Experimental results are presented and compared in terms of area average, radial pitchwise average distributions and exit plane contours of total pressure losses.

To complete the paper, the impact of the results on the design of LP Turbines is discussed and presented.

Copyright © 2012 by ASME
Topics: Mach number , Turbines

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