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
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Figure 1

V64.3A gas turbine meridional view

Grahic Jump Location
Figure 2

Turbine cooling and secondary air flows

Grahic Jump Location
Figure 3

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

Grahic Jump Location
Figure 4

Variation of cp with temperature and fuel∕air ratio

Grahic Jump Location
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

Grahic Jump Location
Figure 6

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

Grahic Jump Location
Figure 7

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

Grahic Jump Location
Figure 8

Computed and measured total temperature at turbine exit



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