Increased availability of natural gas has boosted research and
development efforts to further increase gas turbine performance. Performance
has been increased remarkably and unit cost reduced due to achievements
gained in improving thermodynamic cycles and cooling technologies. However,
increased complexity in power industry regulations and fluctuations in fuel price
have indicated that all the aforementioned improvements in gas turbine
performance could not cope with the increased competition in the gas turbine
industrial market. Innovation within the aero-derivative concept has enabled
further significant improvement in the performance of industrial gas turbines. It
allows a more beneficial approach than developing new designs of industrial
gas turbines owing to reduced designing time and cost. Objectives in this
project focus on developing a methodology of design and assessing aeroderivative
gas turbine engines derived from a 130-seat aircraft engine.
Developed methodology includes techno-economic and environmental
assessment, conducted through further developments of models based on
Techno-economic and Environmental Risk Assessment (TERA) philosophy, to
be applied in further industrial applications.
Tools used in this investigation include a significant literature research on
the development of aero-derivative gas turbine technologies, including
thermodynamic cycles and its land-based applications. Turbomatch is a homebased
code developed in Cranfield University, used in calculating design point
and predicting off-design performance of parent aero-engine and the aeroderivative
engines developed. Excel and FORTRAN code are also used in
calculating engine’s design parameters, and creating a model of life estimation
Creep. Moreover, FORTRAN code is used for building emission and economic
models for power generation and combined heat and power applications.
Finally, MATLAP code is used in creating a small model for generating
performance TXT files, and running marine integrated models platform. All models needed to develop the methodology have been created, and
calculations of an engine’s performance and assessment were conducted
based on this developed methodology. Sensible results are generated from the
investigated methodology and they show acceptable designs of aero-derivative
engines on different thermodynamic cycles. Based on the acceptable level of
technology and material thermal barriers, all design and off-design performance
limitations of new developed aero-derivative engines have been determined for
a wide range of ambient conditions. Techno-economic and environmental
assessment performed through implementing the developed aero-derivative
engines on power generation and marine applications under different operating
scenarios. Results of operating the engines on power generation and marine
applications have been investigated and compared. It is observed that engines
respond differently when operating under different environmental profiles,
depending on the number of units engaged and their thermodynamic cycle as
well as mechanical configurations. Also, the selected specific gas turbine
engine can be the best economical choice for operating on determined
scenario, while it cannot be when operating in different scenarios. Assessment
of developed engines on the investigated application shows how the lowest
specific cost (small engine size) can constitute important criteria in engine
selection.
| Identifer | oai:union.ndltd.org:CRANFIELD1/oai:dspace.lib.cranfield.ac.uk:1826/7929 |
| Date | 08 1900 |
| Creators | Abaad, Abdelmanam |
| Contributors | Pilidis, Pericles |
| Publisher | Cranfield University |
| Source Sets | CRANFIELD1 |
| Language | English |
| Detected Language | English |
| Type | Thesis or dissertation, Doctoral, PhD |
| Rights | © Cranfield University 2011. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright owner. |
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