20 Years Experience Burning Heavy Fuels in Heavy Duty Gas Turbines

1973 ◽  
Author(s):  
A. O. White
Keyword(s):  
Gas Turbines ◽  
Processing System ◽  
Operating Experience ◽  
Field Tests ◽  
Early Experience ◽  
Liquid Fuels ◽  
Heavy Duty ◽  
Fuel Processing ◽  
Wide Range ◽  
Heavy Fuels

This paper covers the early experience of the author’s company in burning residual oils in their gas turbines and the problems that occurred. The laboratory invesgations and field tests that resulted in a fuel processing system that permitted satisfactory operation on a wide range of liquid fuels are described. The operating experiences, where residual fuels were successfully burned in a large number of units, are described. The most recent operating experience with residual and crude oils and heavy distillates is also covered. A list of the various installations with dates and hours of operation is included and it is concluded that heavy duty gas turbines burning heavy fuels will be established as the up-to-date source of economical power in many applications.

CFD Analysis of Turbec T100 Combustor at Part Load by Varying Fuels

2015 ◽  
Author(s):  
Raffaela Calabria ◽  
Fabio Chiariello ◽  
Patrizio Massoli ◽  
Fabrizio Reale
Keyword(s):  
Natural Gas ◽  
Gas Turbines ◽  
Combustion Process ◽  
Calorific Value ◽  
Operating Conditions ◽  
Liquid Fuels ◽  
Cfd Analysis ◽  
Part Load ◽  
Gaseous Fuels ◽  
Wide Range

In recent years an increasing interest is focused on the study of micro gas turbines (MGT) behavior at part load by varying fuel, in order to determine their versatility. The interest in using MGT is related to the possibility of feeding with a wide range of fuels and to realize efficient cogenerative cycles by recovering heat from exhaust gases at higher temperatures. In this context, the studies on micro gas turbines are focused on the analysis of the machine versatility and flexibility, when operating conditions and fuels are significantly varied. In line of principle, in case of gaseous fuels with similar Wobbe Index no modifications to the combustion chamber should be required. The adoption of fuels whose properties differ greatly from those of design can require relevant modifications of the combustor, besides the proper adaptation of the feeding system. Thus, at low loads or low calorific value fuels, the combustor becomes a critical component of the entire MGT, as regards stability and emissions of the combustion process. Focus of the paper is a 3D CFD analysis of the combustor behavior of a Turbec T100P fueled at different loads and fuels. Differences between combustors designed for natural gas and liquid fuels are also highlighted. In case of natural gas, inlet combustor temperature and pressure were taken from experimental data; in case of different fuels, such data were inferred by using a thermodynamic model which takes into account rotating components behavior through operating maps of compressor and turbine. Specific aim of the work is to underline potentialities and critical issues of the combustor under study in case of adoption of fuels far from the design one and to suggest possible solutions.

The Treatment of Marine Heavy Fuels for Gas Turbine Combustion

1972 ◽  
Author(s):  
P. J. Cullen ◽  
T. A. Urbas
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Heavy Duty ◽  
Fuel Treatment ◽  
Gas Turbine Combustion ◽  
Heavy Fuels ◽  
Heavy Duty Gas Turbine

The resurgence of interest in the heavy duty gas turbine for marine use is due in a large part to its ability to burn residual and crude fuels. Generalities involving fuel treatment requirements have been bandied about for years and often the wrong information is used by unknowledgeable individuals when making quotations or bid evaluations. The purpose of this paper is to present firm information on the treatment of marine fuels for heavy duty gas turbines.

A Comparative Analysis of Single Nozzle and Multiple Nozzles Arrangements for Syngas Combustion in Heavy Duty Gas Turbine

2016 ◽  
Vol 139 (2) ◽  
Author(s):  
Shi Liu ◽  
Hong Yin ◽  
Yan Xiong ◽  
Xiaoqing Xiao
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Combined Cycle ◽  
Heavy Duty ◽  
Gas Turbine Combustor ◽  
Integrated Gasification Combined Cycle ◽  
Wide Range ◽  
Heavy Duty Gas Turbine ◽  
Integrated Gasification

Heavy duty gas turbines are the core components in the integrated gasification combined cycle (IGCC) system. Different from the conventional fuel for gas turbine such as natural gas and light diesel, the combustible component acquired from the IGCC system is hydrogen-rich syngas fuel. It is important to modify the original gas turbine combustor or redesign a new combustor for syngas application since the fuel properties are featured with the wide range hydrogen and carbon monoxide mixture. First, one heavy duty gas turbine combustor which adopts natural gas and light diesel was selected as the original type. The redesign work mainly focused on the combustor head and nozzle arrangements. This paper investigated two feasible combustor arrangements for the syngas utilization including single nozzle and multiple nozzles. Numerical simulations are conducted to compare the flow field, temperature field, composition distributions, and overall performance of the two schemes. The obtained results show that the flow structure of the multiple nozzles scheme is better and the temperature distribution inside the combustor is more uniform, and the total pressure recovery is higher than the single nozzle scheme. Through the full scale test rig verification, the combustor redesign with multiple nozzles scheme is acceptable under middle and high pressure combustion test conditions. Besides, the numerical computations generally match with the experimental results.

Parametric Analysis of Existing Gas Turbines With Inlet Evaporative and Overspray Fogging

2005 ◽  
Vol 127 (1) ◽  
pp. 145-158 ◽  
Author(s):  
R. Bhargava ◽  
C. B. Meher-Homji
Keyword(s):  
Gas Turbine ◽  
Performance Improvement ◽  
Gas Turbines ◽  
Parametric Analysis ◽  
Design Parameters ◽  
Performance Parameters ◽  
Heavy Duty ◽  
Wide Range ◽  
The World ◽  
Turbine Design

With deregulation in the power generation market and a need for flexibility in terms of power augmentation during the periods of high electricity demand, power plant operators all over the world are exploring means to augment power from both the existing and new gas turbines. An approach becoming increasingly popular is that of the high pressure inlet fogging. In this paper, the results of a comprehensive parametric analysis on the effects of inlet fogging on a wide range of existing gas turbines are presented. Both evaporative and overspray fogging conditions have been analyzed. The results show that the performance parameters indicative of inlet fogging effects have a definitive correlation with the key gas turbine design parameters. In addition, this study indicates that the aeroderivative gas turbines, in comparison to the heavy-duty industrial machines, have higher performance improvement due to inlet fogging effects. Plausible reasons for the observed trends are discussed. This paper represents the first systematic study on the effects of inlet fogging for a large number (a total of 67) of gas turbines available from the major gas turbine manufacturers.

Operating Experience With the Gas Turbine Powered LNG/Ethylene Carrier “LUCIAN”

1978 ◽  
Author(s):  
K. Naesheim ◽  
W. I. Rowen
Keyword(s):  
Gas Turbine ◽  
Operating Experience ◽  
Dual Fuel ◽  
Heavy Duty ◽  
Paper Briefly ◽  
Wide Range ◽  
Tank System ◽  
Liquefied Gas

The GTV LUCIAN is a 29,000-cu m liquefied gas carrier designed, utilizing the Kvaerner-Moss tank system, as a world trader. The vessel is powered by a 20,000-hp heavy-duty marine gas turbine, equipped to burn a wide range of heavy residual fuels in combination with LNG cargo boil-off. Since entering commmercial service in June 1975, the LUCIAN has traveled almost 150,000 n.m., and accumulated approximately 9000 fired hours on the propulsion machinery. Virtually all of this service occurred using heavy residua fuels, with some operation in a dual-fuel mode with cargo boil-off, when LNG cargo was being carried. This paper briefly describes the vessel and her propulsion machinery, with particular emphasis on those features which are unique to this application. The operating experiences acquired during the last two years are then reviewed. Operating problems encountered with the propulsion machinery are discussed in depth, as are the solutions developed to resolve them.

Operating Experience in Refinery Application of the 13MW-Class Heavy Duty MF-111 Gas Turbine Engine

1990 ◽  
Author(s):  
J. Masada ◽  
I. Fukue
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Operating Experience ◽  
Combined Cycle ◽  
Outlet Temperature ◽  
Heavy Duty ◽  
Turbine Engine ◽  
Industrial Gas Turbines ◽  
Heavy Duty Gas Turbine ◽  
Temperature Levels

A new, 13MW class, heavy duty gas turbine, the “MF-111” was developed for use as a prime mover for cogeneration, combined cycle and repowering applications. The use of such equipment in refineries presents special challenges as regards the combustion of nonstandard fuels, tolerance of industrial environments, and accomodation of site-specific design requirements. Such circumstances add substantially to the tasks of proving and adjusting the design of a new gas turbine, meeting stringent emissions requirements and introducing to the world of industrial gas turbines the benefits of F-class (1250°C burner outlet temperature) levels of thermodynamic performance. This paper describes how these challenges have successfully been met during the three calendar years and ten machine-years of MF-111 refinery-application experience accumulated to-late.

1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part II: Experimental and Theoretical Analysis

1999 ◽  
Vol 122 (3) ◽  
pp. 406-414 ◽  
Author(s):  
Bernhard Ku¨sters ◽  
Heinz-Adolf Schreiber ◽  
Ulf Ko¨ller ◽  
Reinhard Mo¨nig
Keyword(s):  
Boundary Layer ◽  
Gas Turbines ◽  
Total Pressure ◽  
Reynolds Numbers ◽  
Boundary Layer Transition ◽  
Surface Boundary ◽  
Heavy Duty ◽  
High Reynolds Numbers ◽  
Wide Range ◽  
High Reynolds

In Part I of this paper a family of numerically optimized subsonic compressor airfoils for heavy-duty gas turbines, covering a wide range of flow properties, is presented. The objective of the optimization was to create profiles with a wide low loss incidence range. Therefore, design point and off-design performance had to be considered in an objective function. The special flow conditions in large-scale gas turbines have been taken into account by performing the numerical optimization procedure at high Reynolds numbers and high turbulence levels. The objective of Part II is to examine some of the characteristics describing the new airfoils, as well as to prove the reliability of the design process and the flow solver applied. Therefore, some characteristic members of the new airfoil series have been extensively investigated in the cascade wind tunnel of DLR cologne. Experimental and numerical results show profile Mach number distributions, total pressure losses, flow turning, and static pressure rise for the entire incidence range. The design goal with low losses and especially a wide operating range could be confirmed, as well as a mild stall behavior. Boundary layer development, particularly near stall condition, is discussed using surface flow visualization and the results of boundary layer calculations. An additional experimental study, using liquid crystal coating, provides necessary information on suction surface boundary-layer transition at high Reynolds numbers. Finally, results of Navier–Stokes simulations are presented that enlighten the total pressure loss development and flow turning behavior, especially at high incidence in relation to the results of the design tool. [S0889-504X(00)02602-7]

scholarly journals Volatile, Low Lubricity Fuels in Gas Turbine Plants: A Review of Main Fuel Options and Their Respective Merits

1998 ◽  
Author(s):  
M. Molière ◽  
F. Geiger ◽  
E. Deramond ◽  
T. Becker
Keyword(s):  
Power Generation ◽  
Natural Gas ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Alternative Fuels ◽  
Primary Energy ◽  
Liquid Fuels ◽  
Heavy Duty ◽  
Gas Condensates ◽  
Clear Identification

While natural gas is achieving unrivalled penetration in the power generation sector, especially in gas-turbine combined cycles (CCGT), an increasing number of alternative fuels are in a position to take up the ground left vacant by this major primary energy. In particular, within the thriving family of liquid fuels, the class of volatile products opens interesting prospects for clean and efficient power generation in CCGT plants. Therefore, it has become a necessity for the gas turbine industry to extensively evaluate such new fuel candidates, among which: naphtha’s; kerosines; gas condensates; Natural Gas Liquids (NGL) and alcohols are the most prominent representatives. From a technical standpoint, the success of such projects requires both a careful approach to several specific issues (eg: fuel handling & storage, operation safety) and a clear identification of technological limits. For instance, while the purity of gas condensates meets the requirements of heavy-duty technologies, it generally appears unsuitable for aeroderivative machines. This paper offers a succinct but comprehensive technical approach and overviews some experience acquired in this area with heavy duty gas turbines. Its aim is to inform gas turbine users/engineers and project developers who envisage volatile fuels as alternative primary energies in gas turbine plants.

Firing Low Viscosity Liquid Fuels in Heavy Duty Gas Turbines

2003 ◽  
Author(s):  
Jean-Pierre Stalder ◽  
Phil Roberts
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Electrical Energy ◽  
Thermal Capacity ◽  
Transport Infrastructure ◽  
Liquid Fuels ◽  
Light Cycle ◽  
Heavy Duty ◽  
Light Cycle Oil ◽  
Low Viscosity

Sustained economic growth has created a strong demand for electrical energy worldwide. Security of fuel supply and cost are therefore very often critical issues for thermal capacity additions. Also the distance from fuel sources and available fuel transport infrastructure is an important factor in the cost of generation. Many plant locations have only limited supplies of conventional gas turbine fuels, namely natural gas and distillate fuels, thus a drive to diversify the fuels involved. For other electricity producers, the optimal use of existing or potential fuel resources is a must for economical reasons. Therefore, the possibility of using alternative gas turbine liquid fuels, such as volatile and/or low viscosity fuels like naphtha, gas condensates, kerosene, methanol, ethanol, or low lubricity distillate fuels; refinery by-products such as BTX fuels (benzene-toluene-xylene mixtures), LCO-light cycle oil, or in the future synthetic fuels (GTL) are particularly interesting for their ability to be fired in heavy duty gas turbines. However, the practical use of these fuels creates specific issues such as low lubricity properties which can affect sensitive key components like fuel pumps and flow dividers. This paper addresses the many practical aspects of using fuel lubricity additives for reduced component wear in gas turbine fuel systems, and for reliability and successful plant operation on these alternative gas turbine liquid fuels. Also an overview of acquired experience is given.

scholarly journals Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines: Part I — Design and Optimization

1999 ◽  
Author(s):  
Ulf Köller ◽  
Reinhard Mönig ◽  
Bernhard Küsters ◽  
Heinz-Adolf Schreiber
Keyword(s):  
Gas Turbines ◽  
Superior Performance ◽  
Experimental Investigations ◽  
Heavy Duty ◽  
Flow Angle ◽  
Design And Optimization ◽  
New Family ◽  
Blade Thickness ◽  
Wide Range ◽  
The Impact

A new family of subsonic compressor airfoils, which are characterized by low losses and wide operating ranges, has been designed for use in heavy-duty gas turbines. In particular the influence of the higher airfoil Reynolds numbers compared to aeroengine compressors and the impact of these differences on the location of transition are taken into account. The design process itself is carried out by the combination of a geometrical code for the airfoil description, with a blade-to-blade solver and a numerical optimization algorithm. The optimization process includes the design-point losses for a specified Q3D flow problem and the off-design performance for the entire operating range. The family covers a wide range of inlet flow angle, Mach number, flow turning, blade thickness, solidity and AVDR in order to consider the entire range of flow conditions which occur in practical compressor design. The superior performance of the new airfoil family is demonstrated by a comparison with conventional controlled diffusion airfoils (CDA). The advantage in performance has been confirmed by detailed experimental investigations, which will be presented in Part II of the paper. This leads to the conclusion that CDA airfoils which have been primarily developed for aero engine applications are not the optimum solution, if directly transferred to heavy-duty gas turbines. A significant improvement in compressor efficiency is possible, if the new profiles are used instead of conventional airfoils.

Sign in / Sign up

Export Citation Format

Share Document