Abstract
Historically, the development of gas turbine technologies is intrinsically linked with the increase in the initial temperature of the working fluid, which provides an increase in the thermal efficiency and thermodynamic efficiency of the gas turbine cycle. The increase in the gas turbine initial temperature leads to the unit costs reduction and the unit capacity is increased. However, higher turbine inlet parameters increase significantly thermal stresses in the metal, especially during a start-stop operation. In this study we compared the efficiency of three gas turbines with different values of the turbine inlet temperature during covering different parts of the daily electric load curve. The sum of fuel and depreciation costs is chosen as an optimization criterion. Service life parameters were determined for the most thermal stressed gas turbine element, namely the first stage gas turbine blades. To implement the low-cycle fatigue analysis, the numerical simulations were implemented using ANSYS®. The modelling was divided in two stages. Firstly, the fluid dynamics behaviour was analysed around the blade cascade with the aim to determine the thermal state during the whole startstop cycle. In the second stage of calculation, the mechanical loads were added caused by centrifugal force and the fluid flow forces from the working fluid side. To determine depreciation costs, the modified equivalent operating hours principle was used. Obtained results showed that for cyclic operation mode with a high number of start-ups and shutdowns, the costs associated with service life reduction exceed markedly the fuel economy, making turbines with lower turbine inlet temperature more profitable.
Highlights
In recent decades, the development of energy systems has been accompanied by an inherently increasing non-uniformity between the consumption and generation of electricity
The development of gas turbine technologies is intrinsically linked with the increase in the initial temperature of the working fluid, which provides an increase in the thermal efficiency and thermodynamic efficiency of the gas turbine cycle
This study only considered startup and shutdown operations when calculating the depreciation costs, assuming for simplicity of calculation that gas turbines always operate at 100% load
Summary
Citation for published version (APA): Aminov, R. Optimal gas turbine inlet temperature for cyclic operation. Journal of Physics: Conference Series, 1111(1), [012046]. Document Version: Publisher’s PDF, known as Version of Record (includes final page, issue and volume numbers). General rights Copyright and moral rights for the publications made accessible in the public portal are retained by the authors and/or other copyright owners and it is a condition of accessing publications that users recognise and abide by the legal requirements associated with these rights. To cite this article: R Z Aminov et al 2018 J. Ser. 1111 012046 View the article online for updates and enhancements. This content was downloaded from IP address 80.100.206.219 on 26/01/2019 at 11:59
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
