Numerical and Experimental Investigations of Combustion Instability Phenomena in Gas Turbine Burners for Heavy Duty and Aero-Engine Applications

2011 ◽  
Author(s):  
Daniele Accornero ◽  
Mario Caruggi ◽  
Alessandro Nilberto ◽  
Ferruccio Pittaluga
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Combustion Instability ◽  
Experimental Investigations ◽  
Heavy Duty ◽  
Analysis And Design ◽  
Research Activities ◽  
Aero Engine ◽  
The Stability ◽  
Combustion Processes

In the recent years, as the technical developments in the field of GT related technology are more and more driven by regulations on environmental pollution control, a whole series of different industrial evolution and innovation lines are investigated so to make combustion processes ever “cleaner”. Among those, there is for sure the adoption of lean and ultra lean combustion processes to be pursued by means of air-fuel premixing combustion technologies. Within this scenario, at DIMSET/SCL (Savona Combustion Laboratory, Dept. of Thermal Machines, Energy Systems and Transportation, Univ. of Genoa) since several years research activities are carried out, mainly within the frame of EC-funded Research Programmes (ICLEAC, MUSCLES, TLC, H2-IGCC) and cooperation with industrial companies of the energy sector (Ansaldo Energia S.p.A.) and aero-propulsion (Avio Group) sectors. Research activities can take advantage of a close integration between experimental facilities, such as several reactive and non-reactive dedicated burner test-rigs, instrumented with LDV, PDA and PIV laser-based equipment, as well as of in-house continuously improved reactive Navier-Stokes solvers for combustor analysis (NastComb solver) and design (TPM method). The paper deals with the stability characterisation of the different combustion-processes taking place within several GT power plants, namely, the heavy duty AE64-3A heavy duty gas turbine (Ansaldo Energia), already present on the market, the so-called Liquid and Gas Rapid Pre-Mix burners, LRPM and GRPM, designed at DIMSET/SCL and still prototypical, and the Avio-designed LPP (Lean Premixed Prevaporised) burner, for aero-engine applications. The research has been addressed at in-depth characterising the stability behaviour of the burner’s operation. In particular, those aspects have been investigated deemed of greatest importance in affecting a stable performance profile, such as swirlers’ design, burner’s internal aerodynamics, premixing duct configuration, fuel typology and injection modalities, etc. The paper gives a synoptic view both of the research approaches (experimental, instrumental, numerical analysis and design) jointly pursued by DIMSET/SCL team in investigating the combustion instability, as well as of the obtained results, which help in pointing out those burner design and operational parameters which appear as most critical in affecting instability insurgence and self-sustainment.

scholarly journals Automated Virtual Testing Rig Incorporating Multi-level Models of Gas Turbine Engines

2018 ◽  
Vol 220 ◽  
pp. 03001
Author(s):  
Andrey Tkachenko ◽  
Ilia Krupenich ◽  
Evgeny Filinov ◽  
Yaroslav Ostapyuk
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Educational Process ◽  
Turbine Engines ◽  
Experimental Investigations ◽  
Gas Turbine Engines ◽  
Engine Operation ◽  
Virtual Testing ◽  
Research Activities ◽  
Multi Level

This article describes the multi-level approach to developing the virtual testing rig of gas turbine engines and power plants. The described virtual rig is developed on the basis of computer-aided system of thermogasdynamic calculations and analysis ASTRA, developed at Samara National Research University. Existing testing rig is widely used in educational process to supply the students’ research activities with the information on engine operation in a variety of ambient and flight conditions during transients. An approach to upgrading the virtual testing rig is proposed. The described modifications would provide the capabilities to solve more complex research tasks, including investigation of influence of geometry of engine elements on the engine characteristics, multidisciplinary investigations, identification of engine models using the results of experimental investigations and identification of sources of engine deficiencies during the development phase of engine designing.

Performance of Gas Turbine Power Plants Controlled by Multiagent Scheme

2006 ◽  
Author(s):  
Lorenzo Dambrosio ◽  
Marco Mastrovito ◽  
Sergio M. Camporeale
Keyword(s):  
Artificial Intelligence ◽  
Gas Turbine ◽  
System Approach ◽  
Power Plants ◽  
Multiagent System ◽  
Control Process ◽  
Control Algorithms ◽  
Load Reduction ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine

In latter years the idea of artificial intelligence has been focused around the concept of a rational agent. An agent is a (software or hardware) entity that can receive signals from the environment and act upon that environment through output signals. In general an agent always tries to carry out an appropriate task. Seldom agents are considered as stand-alone systems. Their main strength can be found in the interaction with other agents in several different ways in a multiagent system. In the present work, multiagent system approach will be used to manage the control process of a single-shaft heavy-duty gas turbine in Multi Input Multi Output mode. The results will show that the multiagent approach to the control problem effectively counteracts the load reduction (including the load rejection condition) with limited overshoot in the controlled variables (as other control algorithms do) while showing good level adaptivity readiness, precision, robustness and stability.

Low DP FlameSheet™ Extended Validation of a Flexible, Low Emissions, Higher Output and Efficiency F-Class Turbine Upgrade

2020 ◽  
Author(s):  
Hany Rizkalla ◽  
Timothy Hui ◽  
Fred Hernandez ◽  
Matthew Yaquinto ◽  
Ramesh KeshavaBhattu
Keyword(s):  
Gas Turbine ◽  
Shale Gas ◽  
Power Plants ◽  
Heat Rate ◽  
Combined Cycle ◽  
Energy Market ◽  
Heavy Duty ◽  
Ambient Conditions ◽  
Rate Improvement ◽  
Combustion Systems

Abstract Renewables proliferation in the energy market is driving the need for flexibility in gas fired power plants to enable a wider and emissions compliant operability range. The ability for a gas fired plant to peak fire while maintaining emissions compliance, full life interval capability, improved simple and combined cycle heat rate and the ability to achieve extended turndown, positions a gas fired asset to benefit from an improved capacity factor, and overall economic viability in an increasingly renewables’ dependent energy market. The low pressure drop FlameSheet™ combustor variant’s implementation alongside PSM’s Gas Turbine Optimization Package (GTOP3.1) on a commercially operating frame 7FA heavy duty gas turbine in 2018 and as introduced in GT2019-91647, is presented with emphasis on extended validation of operational and emissions/tuning performance at different ambient conditions, higher peak firing and minimum load after one year of continuous commercial operation. The output and heat rate improvement achieved with the FlameSheet™/GTOP3.1 conversion thus enabling improved capacity is also discussed. As shale gas continue to grow as a dominant source of the U.S Natural gas supply, the need for fuel flexible combustion systems enabling tolerance to higher ethane/ethylene concentrations associated with Shale gas is required for improved operability. The adverse impact and means to mitigate such higher ethane/ethylene content on standard F-Class heavy duty combustion systems is also presented as part of said FlameSheet™/GTOP 3.1 conversion.

Enhancing Reliability and Reducing O&M Expenditures in Advanced Combined Cycle Gas Turbine Power Plants

2001 ◽  
Author(s):  
V. Kallianpur ◽  
E. Akita ◽  
Y. Tsukuda
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Power Plants ◽  
Material Selection ◽  
Combined Cycle ◽  
Design Tools ◽  
Balanced Approach ◽  
Engine Design ◽  
The Us ◽  
Aero Engine

Explosive growth in power plants in the US and elsewhere is occurring through combined cycle advanced gas turbine technology. Significant fuel expenditure savings are possible through such technology. Much of the recent advances have been possible through the transfer of aero engine design tools, elevated temperature materials, coatings, and sealing technologies. A balanced approach that melds the aero engine technologies and longstanding field experience from large industrial frame gas turbines is key to ensuring Reliability, Availability, Maintainability and Durability (RAM-D) design objectives are met. Future costs associated with power generation and distribution with these advanced gas turbine combined cycle power plants will undoubtedly be driven by major decisions of OEMs pertaining to design and validation approach, material selection, reparability, design criteria, and design features for quicker maintainability. In this paper, MHI’s approach for enhancing RAM-D performance and reducing O&M expenditures of advanced combined cycle gas turbines are described.

Performance of Gas Turbine Power Plants Controlled by the Multiagent Scheme

2006 ◽  
Vol 129 (3) ◽  
pp. 738-745 ◽  
Author(s):  
Lorenzo Dambrosio ◽  
Marco Mastrovito ◽  
Sergio M. Camporeale
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Multiagent System ◽  
Control Algorithms ◽  
Load Reduction ◽  
Heavy Duty ◽  
Inlet Guide Vanes ◽  
Turbine Efficiency ◽  
Power Frequency ◽  
Heavy Duty Gas Turbine

In recent years the idea of artificial intelligence has been focused around the concept of rational agent. An agent is an (software or hardware) entity that can receive signals from the environment and act upon that environment through output signals, trying to carry out an appropriate task. Seldom agents are considered as stand-alone systems; on the contrary, their main strength can be found in the interaction with other agents, constituting the so-called multiagent system. In the present work, a multiagent system was chosen as a control system of a single-shaft heavy-duty gas turbine in the multi input multi output mode. The shaft rotational speed (power frequency) and stack temperature (related to the overall gas turbine efficiency) represent the controlled variables; on the other hand, the fuel mass flow (VCE) and the variable inlet guide vanes (VIGV) have been chosen as manipulating variables. The results show that the multiagent approach to the control problem effectively counteracts the load reduction (including the load rejection condition) with limited overshoot in the controlled variables (as other control algorithms do) while showing a good level of adaptivity, readiness, precision, robustness, and stability.

scholarly journals A neuro-fuzzy controller for grid-connected heavy-duty gas turbine power plants

2017 ◽  
Vol 25 ◽  
pp. 2375-2387 ◽  
Author(s):  
Mohamed Mustafa MOHAMED IQBAL ◽  
Rayappan JOSEPH XAVIER ◽  
Jagannathan KANAKARAJ
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Fuzzy Controller ◽  
Heavy Duty ◽  
Neuro Fuzzy ◽  
Heavy Duty Gas Turbine

Development and Assessment of Combustion Models for Gas Turbine and Aero-Engine Applications

2015 ◽  
Author(s):  
Jan E. Anker ◽  
Dirk Wunsch ◽  
Luigi Romagnosi ◽  
Kilian Claramunt ◽  
Charles Hirsch
Keyword(s):  
Gas Turbine ◽  
Combustion Process ◽  
Measurement Data ◽  
Point Of View ◽  
Navier Stokes ◽  
Flammability Limits ◽  
Combustion Models ◽  
Spray Flames ◽  
Aero Engine ◽  
Combustion Processes

The classical flamelet method, the new Flamelet Generated Manifolds method (FGM), and the hybrid BML/flamelet approach are assessed in the context of the Reynolds-averaged Navier-Stokes (RANS) equations on a large range of configurations for both gaseous and spray flames. The conceptual differences, advantages, and shortcomings of the models are discussed in detail both from a theoretical and a practical point of view. In order to assess the models under gas turbine like conditions, the reactive flow in TU Darmstadt’s Generic Gas Turbine (GGT), DLR Stuttgart’s PRECCINSTA burner, and a premixed industrial combustor are computed. The computational results are compared to available measurement data and are used to discuss the strengths and the weaknesses of each of the aforementioned combustion models. In the current study it is shown that the hybrid BML/flamelet method globally performs well, but that it can be difficult to obtain a burning solution with this method, especially when the combustion process is operated close to the flammability limits. While the flamelet method is very robust, it is outperformed by the FGM method even for purely non-premixed configurations. It is demonstrated that the FGM approach can be used for the whole range of combustion modes, from non-premixed over to premixed combustion processes. Since the model did not lead to any difficulties with attaining a burning solution, and is computationally as efficient as the flamelet approach, the authors recommend the usage of this model over the other models investigated.

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