Gas turbines are often required to operate at different power levels and under varying environmental conditions. But by the nature of the thermodynamic processes in the engine, it is not possible to obtain the same level of efficiency within the entire range of operation. Therefore, depending on the particular application, for example for power generation, the rotational speed would be constant and dictated by the electrical generating machine. Gas turbine engine consists of various components which are linked together in such a way that there exists a mechanical and thermodynamic interdependence among some components. This means that some operational compatibility (matching) between components will be required for a steady state or equilibrium operation. The steady state of gas turbine engine for power generation can be achieved by the matching of its compressor and turbine. The usual approach of matching the compressor and the turbine is usually based on using an iterative procedure to determine the turbine operating points which are then plotted on the compressor characteristics. The draw back of this process is being laborious and time consuming. The new approach developed overcomes this by superimposing the turbine performance characteristics on the compressor performance characteristics while meeting the components matching conditions. This can be done by introducing a new mass flow dimensionless parameter. Superimposing the turbine map on the compressor map cannot be totally accepted until both maps axes (the abscissa and the ordinate) are identical. This paper explains the new approach adopted to a single shaft gas turbine engine. Theoretically, the developed techniques can be applied to other gas turbine engines.
| Published in | International Journal of Mechanical Engineering and Applications (Volume 5, Issue 4) |
| DOI | 10.11648/j.ijmea.20170504.15 |
| Page(s) | 214-222 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2024. Published by Science Publishing Group |
Gas Turbine Off-Design, Gas Turbine Performance, Component Matching
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| [2] | Kong C., Ki J., Kang M., “Fuzzy approaches for searching optimal component matching point in gas turbine performance simulation”, J. Eng. Gas Turbines Power, Vol. 126, issue 4, (2004), 741-747. |
| [3] | Gugau M., and Roclawski, H., “On the Design and Matching of Turbocharger Single Scroll Turbines for Pass Car Gasoline Engines, J. Eng. Gas Turbines Power, Vol. 136, Issue 12, (2014). |
| [4] | Tsoutsanis E., Meskin N., Benammar M., Khorasani K., “An Efficient Component Map Generation Method for Prediction of Gas Turbine Performance” ASME Turbo Expo 2014: Turbine Technical Conference and Exposition Volume 6: Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy, Düsseldorf, Germany, June 16–20, 2014. |
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APA Style
Munzer S. Y. Ebaid, Qusai Z. Al-Hamdan. (2017). A New Approach of Gas Turbine Component Matching for Electrical Power Generation. International Journal of Mechanical Engineering and Applications, 5(4), 214-222. https://doi.org/10.11648/j.ijmea.20170504.15
ACS Style
Munzer S. Y. Ebaid; Qusai Z. Al-Hamdan. A New Approach of Gas Turbine Component Matching for Electrical Power Generation. Int. J. Mech. Eng. Appl. 2017, 5(4), 214-222. doi: 10.11648/j.ijmea.20170504.15
AMA Style
Munzer S. Y. Ebaid, Qusai Z. Al-Hamdan. A New Approach of Gas Turbine Component Matching for Electrical Power Generation. Int J Mech Eng Appl. 2017;5(4):214-222. doi: 10.11648/j.ijmea.20170504.15
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Download@article{10.11648/j.ijmea.20170504.15,
author = {Munzer S. Y. Ebaid and Qusai Z. Al-Hamdan},
title = {A New Approach of Gas Turbine Component Matching for Electrical Power Generation},
journal = {International Journal of Mechanical Engineering and Applications},
volume = {5},
number = {4},
pages = {214-222},
doi = {10.11648/j.ijmea.20170504.15},
url = {https://doi.org/10.11648/j.ijmea.20170504.15},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.20170504.15},
abstract = {Gas turbines are often required to operate at different power levels and under varying environmental conditions. But by the nature of the thermodynamic processes in the engine, it is not possible to obtain the same level of efficiency within the entire range of operation. Therefore, depending on the particular application, for example for power generation, the rotational speed would be constant and dictated by the electrical generating machine. Gas turbine engine consists of various components which are linked together in such a way that there exists a mechanical and thermodynamic interdependence among some components. This means that some operational compatibility (matching) between components will be required for a steady state or equilibrium operation. The steady state of gas turbine engine for power generation can be achieved by the matching of its compressor and turbine. The usual approach of matching the compressor and the turbine is usually based on using an iterative procedure to determine the turbine operating points which are then plotted on the compressor characteristics. The draw back of this process is being laborious and time consuming. The new approach developed overcomes this by superimposing the turbine performance characteristics on the compressor performance characteristics while meeting the components matching conditions. This can be done by introducing a new mass flow dimensionless parameter. Superimposing the turbine map on the compressor map cannot be totally accepted until both maps axes (the abscissa and the ordinate) are identical. This paper explains the new approach adopted to a single shaft gas turbine engine. Theoretically, the developed techniques can be applied to other gas turbine engines.},
year = {2017}
}
TY - JOUR T1 - A New Approach of Gas Turbine Component Matching for Electrical Power Generation AU - Munzer S. Y. Ebaid AU - Qusai Z. Al-Hamdan Y1 - 2017/08/04 PY - 2017 N1 - https://doi.org/10.11648/j.ijmea.20170504.15 DO - 10.11648/j.ijmea.20170504.15 T2 - International Journal of Mechanical Engineering and Applications JF - International Journal of Mechanical Engineering and Applications JO - International Journal of Mechanical Engineering and Applications SP - 214 EP - 222 PB - Science Publishing Group SN - 2330-0248 UR - https://doi.org/10.11648/j.ijmea.20170504.15 AB - Gas turbines are often required to operate at different power levels and under varying environmental conditions. But by the nature of the thermodynamic processes in the engine, it is not possible to obtain the same level of efficiency within the entire range of operation. Therefore, depending on the particular application, for example for power generation, the rotational speed would be constant and dictated by the electrical generating machine. Gas turbine engine consists of various components which are linked together in such a way that there exists a mechanical and thermodynamic interdependence among some components. This means that some operational compatibility (matching) between components will be required for a steady state or equilibrium operation. The steady state of gas turbine engine for power generation can be achieved by the matching of its compressor and turbine. The usual approach of matching the compressor and the turbine is usually based on using an iterative procedure to determine the turbine operating points which are then plotted on the compressor characteristics. The draw back of this process is being laborious and time consuming. The new approach developed overcomes this by superimposing the turbine performance characteristics on the compressor performance characteristics while meeting the components matching conditions. This can be done by introducing a new mass flow dimensionless parameter. Superimposing the turbine map on the compressor map cannot be totally accepted until both maps axes (the abscissa and the ordinate) are identical. This paper explains the new approach adopted to a single shaft gas turbine engine. Theoretically, the developed techniques can be applied to other gas turbine engines. VL - 5 IS - 4 ER -
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