Research Papers

A Redesign Strategy to Improve the Efficiency of a 17-Stage Steam Turbine

[+] Author and Article Information
Filippo Rubechini

“Sergio Stecco” Department of Energy Engineering, University of Florence, Via di Santa Marta 3, 50139 Firenze, Italyfilippo.rubechini@arnone.de.unifi.it

Andrea Schneider, Andrea Arnone

“Sergio Stecco” Department of Energy Engineering, University of Florence, Via di Santa Marta 3, 50139 Firenze, Italy

Stefano Cecchi

 Ansaldo Energia, Via N. Lorenzi 8, 16152 Genova, Italystefano.cecchi@aen.ansaldo.it

Francesco Malavasi

 Ansaldo Energia, Via N. Lorenzi 8, 16152 Genova, Italy

J. Turbomach 134(3), 031021 (Jul 15, 2011) (7 pages) doi:10.1115/1.4003082 History: Received June 16, 2009; Revised August 23, 2010; Published July 15, 2011; Online July 15, 2011

A three-dimensional Reynolds averaged Navier–Stokes solver was applied to the aerodynamic redesigning of a 17-stage steam turbine. The redesign procedure was divided into three steps. In the first one, a single embedded stage was considered, and an optimization of stator lean and rotor twist was carried out by applying suitable repeating inlet/outlet boundary conditions. In the second step, a proper geometrical transformation between the original reference stage and the optimized one was identified and then applied to all other turbine stages, thus leading to a first approximation of the redesigned turbine. Finally, a neural-network-based refinement of the stator and rotor twist of each stage was performed to account for its actual position and operating conditions within the meridional channel. In this work, a detailed description of the redesign procedure is provided, and the aerodynamic characteristics of the optimized geometry are discussed and compared with the original ones.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Meridional view of the IP steam turbine

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Figure 4

Stator lean modification (from single-stage optimization)

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Figure 5

Spanwise distributions of static pressure (stage 06). Comparison between original and G0128 geometry.

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Figure 6

Results of three-stage computations: comparison between original and G0128 geometry

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Figure 7

Stage by stage stagger distributions. Stagger angles are given with respect to the first stage value at hub.

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Figure 8

Computed and artificial neural network suggested solutions

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Figure 9

Stage by stage stagger departures from G0128

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Figure 10

Spanwise distributions of static pressure (stage 06). Comparison between original, intermediate, and final turbines.

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Figure 11

Stage by stage distributions of efficiency, pressure drop, and leakage mass flow

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Figure 12

Stage by stage distribution of stage reaction and streamwise variation in throat area with respect to original turbine

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Figure 3

Impact of shroud leakage. Spanwise swirl angle distribution with and without leakage.

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Figure 2

IP turbine geometry (stage 06). Midspan airfoil sections and geometrical changes under investigation.




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