Abstract
The objective of this work is the characterization of the performance of complex gas turbine cycles that include several compressions with intercooling stages, followed by two or more combustionexpansion sections. Explicit relationships are presented to compute the power output, the thermal efficiency and the optimum pressure ratio values as functions of the gas temperatures at the entrance of the turbine and of the air at the entrance of the compressor, of the isentropic compression and expansion efficiencies, and the number of compression and expansion stages, NC and NT. Parametric curves showing the optimum pressure ratio to obtain maximum power and maximum thermal are presented for each of the cases studied in this work. For complex turbines, the optimum pressure ratios are in an acceptable range, between 8.1 and 23.1 for the maximum power and between 17.4 and 32.2 for the maximum thermal efficiency.
| Translated title of the contribution | Optimum pressure ratio for complex gas turbine cycles |
|---|---|
| Original language | Spanish |
| Pages (from-to) | 137-151 |
| Number of pages | 15 |
| Journal | Informacion Tecnologica |
| Volume | 20 |
| Issue number | 6 |
| DOIs | |
| State | Published - 2009 |