Optimization of a Regenerative Gas Turbine Engine With Isothermal Heat Addition With the Genetic Algorithm

2009 ◽  
Author(s):  
E. Haghighi ◽  
B. Borzou ◽  
Amir R. Ghahremani ◽  
M. Behshad Shafii
Keyword(s):  
Genetic Algorithm ◽  
Gas Turbine ◽  
Large Scale ◽  
Thermodynamic Characteristics ◽  
Gas Turbine Engine ◽  
Engineering Problem ◽  
Turbine Engine ◽  
Heat Addition ◽  
Advanced Cycles ◽  
Gas Turbine Cycle

The use of advanced cycles to take advantage of the gas turbine’s thermodynamic characteristics has received increasing attention in recent years. These cycles have been developed for large scale power generation. Due to the powerful abilities of bio-inspired computing techniques such as Genetic Algorithm in locating the optimal (or near optimal) solutions to a given optimization problem, they are widely utilized for determining the parameters of different engineering systems in order to meet the specified performance objectives for a given problem. In order to illustrate the performance of one of these techniques, development and application of it for an engineering problem is presented. In this paper a regenerative gas turbine cycle, with isothermal heat addition has been analyzed. The optimization of system has been carried out numerically using the Genetic Algorithm method. Results show that the regenerative gas turbine engine, with isothermal heat addition, designed according to the optimum parameters condition gives the best performance and exhibits highest cycle efficiencies.

scholarly journals Stability Analysis of Multiharmonic Nonlinear Vibrations for Large Models of Gas-Turbine Engine Structures With Friction and Gaps

2016 ◽  
Author(s):  
E. P. Petrov
Keyword(s):  
Gas Turbine ◽  
Large Scale ◽  
Frequency Domain Analysis ◽  
Gas Turbine Engine ◽  
Forced Response ◽  
Scale Model ◽  
Turbine Engine ◽  
Nonlinear Springs ◽  
Large Scale Model ◽  
The Stability

An efficient method is proposed for the multiharmonic frequency domain analysis of the stability for nonlinear periodic forced vibrations in gas-turbine engine structures and turbomachines with friction, gaps and other types of nonlinear contact interfaces. The method allows using large-scale finite element models for structural components together with detailed description of nonlinear interactions at contact interfaces between these components. The highly accurate reduced models are applied in the assessment of stability of periodic regimes for large-scale model of gas-turbine structures. An approach is proposed for the highly-accurate calculation of motion of a structure after it is perturbed from the periodic nonlinear forced response. Efficiency of the developed approach is demonstrated on a set of test cases including simple models and large-scale realistic bladed disc models with different types of nonlinearities: friction, gaps and cubic nonlinear springs.

Optimization of a Gas Turbine Engine Rotor Disc Using Case-Based Reasoning and the GATE Genetic Algorithm

2010 ◽  
Author(s):  
S. Dominique ◽  
J.-Y. Tre´panier
Keyword(s):  
Genetic Algorithm ◽  
Gas Turbine ◽  
Structural Design ◽  
Gas Turbine Engine ◽  
Pattern Search ◽  
Case Based Reasoning ◽  
Turbine Engine ◽  
Local Searches ◽  
Case Based ◽  
Engine Rotor

The implementation of an automated decision support system in the field of structural design and optimization can give a significant advantage to any industry working on mechanical design. Such a system can reduce the project cycle time or allow more time to produce a better design by providing solution ideas to a designer or by upgrading existing design solutions while the designer is not at work. This paper presents an approach to automating the process of designing a gas turbine engine rotor disc using case-based reasoning (CBR), combined with a new genetic algorithm, the Genetic Algorithm with Territorial core Evolution (GATE). GATE was specifically created to solve problems in the mechanical structural design field, and is essentially a real number genetic algorithm that prevents new individuals from being born too close to previously evaluated solutions. The restricted area becomes smaller or larger during optimization to allow global or local searches when necessary. The CBR process uses a databank filled with every known solution to similar design problems. The closest solutions to the current problem in terms of specifications are selected, along with an estimated solution from an artificial neural network. Each solution selected by the CBR is then used to initialize the population of a GATE island. Our results show that CBR may significantly upgrade the performance of an optimization algorithm when sufficient preliminary information is known about the design problem. It provides an average solution 5.0% lighter than the average solution found using random initialization. The results are compared to other results obtained for the same problems by four optimization algorithms from the I-SIGHT 3.5 software: the sequential quadratic programming algorithm (SQP), the insular genetic algorithm (GA), the Hookes & Jeeves generalized pattern search (HJ) and POINTER. Results show that GATE can be a very good candidate for automating and accelerating the structural design of a gas turbine engine rotor disc, providing an average disc 18.9% lighter than SQP, 11.2% lighter than HJ, 23.9% lighter than GA and 4.3% lighter than POINTER, even when starting with the same solution set.

Thermodynamic Analysis of Integrated Molten Carbon Fuel Cell–Gas Turbine Cycles for Sub-MW and Multi-MW Scale Power Generation

2006 ◽  
Vol 4 (3) ◽  
pp. 308-316 ◽  
Author(s):  
S. Campanari ◽  
P. Iora ◽  
P. Silva ◽  
E. Macchi
Keyword(s):  
Fuel Cell ◽  
Gas Turbine ◽  
Large Scale ◽  
Variable Pressure ◽  
Small Scale ◽  
Inlet Temperature ◽  
Electrical Efficiency ◽  
Internal Reforming ◽  
Advanced Cycles ◽  
Gas Turbine Cycle

This paper investigates the thermodynamic potential of the integration of molten carbon fuel cell (MCFC) technology with gas turbine systems for small-scale (sub-megawatt or sub-MW) as well as large-scale (multi-MW) hybrid cycles. Following the proposals of two important MCFC manufacturers, two plant layouts are discussed, the first based on a pressurized, externally reformed MCFC and a recuperated gas turbine cycle and the second based on an atmospheric MCFC, with internal reforming integrated within an externally fired gas turbine cycle. Different levels of components quality are considered, with an analysis of the effects of variable pressure ratios, different fuel mixture compositions (variable steam-to-carbon ratio) and turbine inlet temperature levels, together with potential advantages brought about by an intercooled compression process. The analysis shows interesting effects due to the peculiarity of the mutual interactions between gas turbine cycle and fuel cells, evidencing the importance of a careful thermodynamic optimization of such cycles. Results show the possibility to achieve a net electrical efficiency of about 57–58% for a small plant size (with a difference of 1.5–2 percentage points between the two layouts), with the potential to reach a 65% net electrical efficiency when integrated in advanced cycles featuring high-efficiency, large-scale equipment (multi-MW scale cycles).

A Genetic Algorithm Approach to Estimate Performance Status of Gas Turbines

2008 ◽  
Author(s):  
Y. G. Li
Keyword(s):  
Genetic Algorithm ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Performance Status ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Accurate Estimation ◽  
Performance Parameters ◽  
Turbine Engine ◽  
Design Point

Accurate estimation of performance status of a gas turbine engine at certain ambient and operating condition based on measured gas path parameters is very important for both engine designers and users alike. It could be a very challenging task for engine performance engineers to estimate the value of component design parameters in order to match measured gas path parameters when the number of design point component parameters and the number of measurable performance parameters become large. Such status estimation can be used to distinguish the performance difference among fleet engines and build accurate engine models at an artificial design point for individual engines, which is also crucially important for gas path diagnostic analysis. In this paper, a gas turbine design point performance adaptation approach based on the integration of gas turbine thermodynamic performance modelling and a Genetic Algorithm has been developed in order to estimate the design point component parameters and match the available gas path measurements of real engines. In the approach, the initially unknown component parameters may be compressor pressure ratios and efficiencies, turbine entry temperature, turbine efficiencies, air mass flow rate, cooling flows, by-pass ratio, etc. The engine measurable performance parameters may be thrust and specific fuel consumption for aero engines, shaft power and thermal efficiency for industrial engines, gas path pressures and temperatures, etc. The developed adaptation approach has been applied to a design point performance status estimation of an industrial gas turbine engine GE LM2500+ operating in Manx Electricity Authority (MEA), UK. The application shows that the adaptation approach is very effective and robust in producing a model engine that matches the actual engine performance with acceptable computation speed. Theoretically the developed techniques can be applied to different gas turbine engines.

Optimal design of the regenerative gas turbine engine with isothermal heat addition

2001 ◽  
Vol 68 (3) ◽  
pp. 249-264 ◽  
Author(s):  
L.Berrin Erbay ◽  
Selahattin Göktun ◽  
Hasbi Yavuz
Keyword(s):  
Optimal Design ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Heat Addition

scholarly journals Stability Analysis of Multiharmonic Nonlinear Vibrations for Large Models of Gas Turbine Engine Structures With Friction and Gaps

2016 ◽  
Vol 139 (2) ◽  
Author(s):  
E. P. Petrov
Keyword(s):  
Gas Turbine ◽  
Large Scale ◽  
Frequency Domain Analysis ◽  
Gas Turbine Engine ◽  
Forced Response ◽  
Scale Model ◽  
Turbine Engine ◽  
Nonlinear Springs ◽  
Large Scale Model ◽  
The Stability

An efficient method is proposed for the multiharmonic frequency-domain analysis of the stability for nonlinear periodic forced vibrations in gas turbine engine structures and turbomachines with friction, gaps, and other types of nonlinear contact interfaces. The method allows using large-scale finite element models for structural components together with detailed description of nonlinear interactions at contact interfaces between these components. The highly accurate reduced models are applied in the assessment of stability of periodic regimes for large-scale model of gas turbine structures. An approach is proposed for the highly accurate calculation of motion of a structure after it is perturbed from the periodic nonlinear forced response. Efficiency of the developed approach is demonstrated on a set of test cases including simple models and large-scale realistic bladed disk models with different types of nonlinearities: friction, gaps, and cubic nonlinear springs.

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