Retracted: “Multi-Objective Aerodynamic Optimisation of a Real Gas Radial-Inflow Turbine” [ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, Volume 2C: Turbomachinery, Seoul, South Korea, June 13–17, 2016, Conference Sponsors: International Gas Turbine Institute, ISBN: 978-0-7918-4971-2, Copyright © 2016 by ASME. Paper No. GT2016-58132, pp. V02CT45A032; 9 pages; doi:10.1115/GT2016-58132]

2016 ◽  
Author(s):  
ASME
Keyword(s):  
South Korea ◽  
Gas Turbine ◽  
Technical Conference ◽  
Real Gas ◽  
Multi Objective ◽  
Asme Turbo Expo ◽  
Radial Inflow Turbine ◽  
Asme Paper

The above referenced paper has been removed from publication. June 29, 2017. Copyright © 2017 by ASME

scholarly journals Erratum: “Forced Response Analysis of a Mistuned Compressor Blisk Comparing Three Different Reduced Order Model Approaches” [ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, Volume 7A: Structures and Dynamics, Seoul, South Korea, June 13–17, 2016, Conference Sponsors: International Gas Turbine Institute, ISBN: 978-0-7918-4983-5, Copyright © 2016 by ASME. Paper No. GT2016-57902, pp. V07AT32A030; 12 pages; doi:10.1115/GT2016-57902]

2016 ◽  
Author(s):  
Mauricio Gutierrez Salas ◽  
Ronnie Bladh ◽  
Hans Mårtensson ◽  
Paul Petrie-Repar ◽  
Torsten Fransson ◽  
...  
Keyword(s):  
South Korea ◽  
Gas Turbine ◽  
Technical Conference ◽  
Forced Response ◽  
Reduced Order Model ◽  
Response Analysis ◽  
Order Model ◽  
Reduced Order ◽  
Asme Turbo Expo ◽  
Asme Paper

This erratum corrects errors that appeared in the paper “Forced Response Analysis of a Mistuned Compressor Blisk Comparing Three Different Reduced Order Model Approaches” which was published in Proceedings of ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, Volume 7A: Structures and Dynamics, V07AT32A030, June 2016, GT2016-57902, doi: 10.1115/GT2016-57902.

scholarly journals Erratum: “Analysis of the Performance of Plasma Actuators Under Low-Pressure Turbine Conditions Based on Experiments and URANS Simulations” [ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, Volume 2A: Turbomachinery, Charlotte, North Carolina, USA, June 26–30, 2017, Conference Sponsors: International Gas Turbine Institute, ISBN: 978-0-7918-5078-7, Copyright © 2017 by ASME. Paper No. GT2017-64867, V02AT40A034; 15 pages; doi: 10.1115/GT2017-64867]

2017 ◽  
Author(s):  
D. S. Martínez ◽  
E. Pescini ◽  
F. Marra ◽  
M. G. De Giorgi ◽  
A. Ficarella
Keyword(s):  
North Carolina ◽  
Gas Turbine ◽  
Low Pressure ◽  
Technical Conference ◽  
Paper Analysis ◽  
Plasma Actuators ◽  
Low Pressure Turbine ◽  
Asme Turbo Expo ◽  
Asme Paper

Abstract This erratum corrects errors that appeared in the paper “Analysis of the Performance of Plasma Actuators Under Low-Pressure Turbine Conditions Based on Experiments and URANS Simulations” which was published in Proceedings of ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, Volume 2A: Turbomachinery, V02AT40A034, June 2017, GT2017-64867, doi: 10.1115/GT2017-64867.

Multi-objective optimization of a recuperative gas turbine cycle using non-dominated sorting genetic algorithm

2011 ◽  
Vol 225 (8) ◽  
pp. 1041-1051 ◽  
Author(s):  
H Sayyaadi ◽  
H R Aminian
Keyword(s):  
Genetic Algorithm ◽  
Gas Turbine ◽  
Heat Exchangers ◽  
Mixed Integer ◽  
Design Stage ◽  
Tube Length ◽  
Pareto Optimal ◽  
Multi Objective Optimization ◽  
Multi Objective ◽  
Gas Turbine Cycle

A regenerative gas turbine cycle with two particular tubular recuperative heat exchangers in parallel is considered for multi-objective optimization. It is assumed that tubular recuperative heat exchangers and its corresponding gas cycle are in design stage simultaneously. Three objective functions including the purchased equipment cost of recuperators, the unit cost rate of the generated power, and the exergetic efficiency of the gas cycle are considered simultaneously. Geometric specifications of the recuperator including tube length, tube outside/inside diameters, tube pitch, inside shell diameter, outer and inner tube limits of the tube bundle and the total number of disc and doughnut baffles, and main operating parameters of the gas cycle including the compressor pressure ratio, exhaust temperature of the combustion chamber and the air mass flowrate are considered as decision variables. Combination of these objectives anddecision variables with suitable engineering and physical constraints (including NO x and CO emission limitations) comprises a set of mixed integer non-linear problems. Optimization programming in MATLAB is performed using one of the most powerful and robust multi-objective optimization algorithms, namely non-dominated sorting genetic algorithm. This approach is applied to find a set of Pareto optimal solutions. Pareto optimal frontier is obtained, and a final optimal solution is selected in a decision-making process.

CFD Simulation of a Supercritical Carbon Dioxide Radial-Inflow Turbine, Comparing the Results of Using Real Gas Equation of Estate and Real Gas Property File

2016 ◽  
Vol 846 ◽  
pp. 85-90 ◽  
Author(s):  
Mostafa Odabaee ◽  
Emilie Sauret ◽  
Kamel Hooman
Keyword(s):  
Carbon Dioxide ◽  
Supercritical Carbon Dioxide ◽  
Cfd Simulation ◽  
Pressure Ratio ◽  
Computational Cost ◽  
Real Gas ◽  
Table Method ◽  
Radial Inflow Turbine ◽  
Solar Resource ◽  
Supercritical Carbon

The present study explores CFD analysis of a supercritical carbon dioxide (SCO2) radial-inflow turbine generating 100kW from a concentrated solar resource of 560oC with a pressure ratio of 2.2. Two methods of real gas property estimations including real gas equation of estate and real gas property (RGP) file - generating a required table from NIST REFPROP - were used. Comparing the numerical results and time consumption of both methods, it was shown that equation of states could insert a significant error in thermodynamic property prediction. Implementing the RGP table method indicated a very good agreement with NIST REFPROP while it had slightly more computational cost compared to the RGP table method.

Modelling the Air-Cooled Gas Turbine: Part 1 — General Thermodynamics

2001 ◽  
Author(s):  
J. B. Young ◽  
R. C. Wilcock
Keyword(s):  
Gas Turbine ◽  
Performance Prediction ◽  
Real Gas ◽  
Thermal Mixing ◽  
Ideal Gases ◽  
Formal Framework ◽  
Considerable Simplification ◽  
Cycle Efficiency ◽  
General Thermodynamics

This paper is Part I of a study concerned with developing a formal framework for modelling air-cooled gas turbine cycles and deals with basic thermodynamic issues. Such cycles involve gas mixtures with varying composition which must be modelled realistically. A possible approach is to define just two components, air and gas, the latter being the products of stoichiometric combustion of the fuel with air. If these components can be represented as ideal gases, the entropy increase due to compositional mixing, although a true exergy loss, can be ignored for the purpose of performance prediction. This provides considerable simplification. Consideration of three idealised simple cycles shows that the introduction of cooling with an associated thermal mixing loss does not necessarily result in a loss of cycle efficiency. This is no longer true when real gas properties and turbomachinery losses are included. The analysis clarifies the role of the cooling losses and shows the importance of assessing performance in the context of the complete cycle. There is a strong case for representing the cooling losses in terms of irreversible entropy production as this provides a formalised framework, clarifies the modelling difficulties and aids physical interpretation. Results are presented which show the effects on performance of varying cooling flowrates and cooling losses. A comparison between simple and reheat cycles highlights the rôle of the thermal mixing loss. Detailed modelling of the heat transfer and cooling losses is discussed in Part II of this paper.

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