Research Papers

The Impact of Gas Modeling in the Numerical Analysis of a Multistage Gas 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

Michele Marconcini, Andrea Arnone

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

Massimiliano Maritano

 Ansaldo Energia, via Lorenzi 8, 16152 Genova, Italymassimiliano.maritano@aen.ansaldo.it

Stefano Cecchi

 Ansaldo Energia, via Lorenzi 8, 16152 Genova, Italy

J. Turbomach 130(2), 021022 (Mar 25, 2008) (7 pages) doi:10.1115/1.2752187 History: Received November 02, 2006; Revised November 09, 2006; Published March 25, 2008

In this work a numerical investigation of a four stage heavy-duty gas turbine is presented. Fully three-dimensional, multistage, Navier-Stokes analyses are carried out to predict the overall turbine performance. Coolant injections, cavity purge flows, and leakage flows are included in the turbine modeling by means of suitable wall boundary conditions. The main objective is the evaluation of the impact of gas modeling on the prediction of the stage and turbine performance parameters. To this end, four different gas models were used: three models are based on the perfect gas assumption with different values of constant cp, and the fourth is a real gas model which accounts for thermodynamic gas properties variations with temperature and mean fuel∕air ratio distribution in the through-flow direction. For the real gas computations, a numerical model is used which is based on the use of gas property tables, and exploits a local fitting of gas data to compute thermodynamic properties. Experimental measurements are available for comparison purposes in terms of static pressure values at the inlet∕outlet of each row and total temperature at the turbine exit.

Copyright © 2008 by American Society of Mechanical Engineers
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Figure 3

Variation of R, cp, and γ with temperature and fuel∕air ratio through the four stage turbine

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Figure 4

Variation of cp with temperature and fuel∕air ratio

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Figure 5

Gas expansion for the four stage turbine computed with perfect gas (PG) and real gas (RG) models: (a) T−s plane; and (b) p−v plane

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Figure 6

Calculated turbine performance versus gas model (% error relative to RG model)

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Figure 7

Comparison between measured and computed static pressure between rows (hub values)

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Figure 8

Computed and measured total temperature at turbine exit

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Figure 2

Turbine cooling and secondary air flows

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Figure 1

V64.3A gas turbine meridional view




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