Extended Fuel Flexibility Testing of Siemens Industrial Gas Turbines: A Novel Approach

2012 ◽  
Author(s):  
Mats Andersson ◽  
Anders Larsson ◽  
Annika Lindholm ◽  
Jenny Larfeldt
Keyword(s):  
Gas Turbines ◽  
Cost Effective ◽  
Full Scale ◽  
Engine Operation ◽  
Gaseous Fuels ◽  
Novel Approach ◽  
Fuel Flexibility ◽  
Industrial Gas Turbines ◽  
Combustion Monitoring ◽  
Testing Fuel

Opportunity gaseous fuels are of great interest for small and medium sized gas turbines. The variety of gaseous fuels that Siemens Industrial Turbomachinery AB (SIT) is requested to make judgments on is continuously expanding. From such requests follows an increasing need for testing new fuels. The SIT novel approach for fuel flexibility testing, EBIT, has been to combine the single burner rig testing with a full scale engine test to give a cost effective and flexible solution. The combination of the two approaches is accomplished by using a separate feed of testing fuel to one or more burners in a standard gas turbine installation where the other burners use standard fuel from standard fuel system for engine operation. The separate feed of testing fuel can be operated as a slave to engine governor heat demand, but can also be controlled independently. This paper describes how EBIT has been implemented and tested. Combustion monitoring techniques and measurements to check behavior and predictions for full scale engine tests are presented. Results from testing with a blended natural gas with more than 50% of heat input from pentane, C5H12, in a SGT-700 engine shows that the EBIT concept is possible and powerful. The SIT 3rd generation DLE burner proves to be very fuel flexible and tolerant to high levels of pentane in the fuel. Less than 20% increase in NOx emissions can be expected when using pentane rich fuels. The burner is used in the SGT-800 47MW engine and the SGT-700 31MW engine.

Engine Testing Using Highly Reactive Fuels on Siemens Industrial Gas Turbines

2014 ◽  
Author(s):  
Alessio Bonaldo ◽  
Mats Andersson ◽  
Anders Larsson
Keyword(s):  
Gas Turbines ◽  
Fuel Flexibility ◽  
Increased Risk ◽  
Test Engine ◽  
Industrial Gas Turbines ◽  
Fuel Nozzle ◽  
High Concentrations ◽  
Engine Testing ◽  
Combustion Monitoring ◽  
Fuel Components

Siemens Industrial Turbomachinery AB (SIT) Finspong is increasingly asked by customers to consider if a wider range of gas compositions may be operated in its gas turbines. A large part of these fuel compositions contain high concentrations of highly reactive components like hydrogen and ethane. Such fuel compositions are characterized by higher flame speeds than the standard natural gas which introduce increased risk for flashback and premature combustor and/or fuel nozzle distress. The SIT approach for fuel flexibility testing, Experimental Burner In Test engine (EBIT) uses a separate feed for testing a selected fuel composition in one burner in a standard gas turbine installation where the other burners use fuel from the standard fuel system. The separate feed is operated as a slave to engine governor heat demand, but can also be controlled independently. This paper describes how EBIT was used to test the capability of the SIT 3rd generation DLE burner to satisfactorily operate using highly reactive fuel components such as ethane and hydrogen. Combustion monitoring techniques and measurements to check flame behavior and assess flashback potentials of the tested fuel compositions are described. Results from testing show that the SIT 3rd generation DLE burner allows extending the levels of reactive fuel components accepted for operation on the SGT-700 33MW engine and SGT-800 50MW engine.

Fuel Flexibility With Low Emissions in Heavy Duty Industrial Gas Turbines

2010 ◽  
Author(s):  
Predrag Popovic ◽  
Geoffrey Myers ◽  
Joseph Citeno ◽  
Richard Symonds ◽  
Anthony Campbell
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Premixed Combustion ◽  
Heavy Duty ◽  
Gaseous Fuels ◽  
Fuel Flexibility ◽  
Wide Range ◽  
Industrial Gas Turbines ◽  
Combustion Technology ◽  
Industrial Gas Turbine

In the 1990’s GE introduced low-emissions combustion technology primarily for gas turbines burning natural gas (NG) fuel. Today, industrial gas turbine fuels are more diverse than ever. As a result, diverse diffusion and premixed combustion technologies are used to burn gaseous fuels with low emissions. This paper summarizes combustion and gas turbine control challenges when firing diverse fuels, and advancements in technology when burning a wide range of fuels with low emissions.

Development and Integration of the Dual Fuel Combustion System for the MGT Gas Turbine Family

2021 ◽  
Author(s):  
Bernhard Ćosić ◽  
Frank Reiss ◽  
Marc Blümer ◽  
Christian Frekers ◽  
Franklin Genin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Distribution System ◽  
Gas Turbines ◽  
Liquid Fuel ◽  
Fuel Injection ◽  
Liquid Fuels ◽  
Dual Fuel ◽  
Gaseous Fuels ◽  
Supply And Distribution ◽  
Industrial Gas Turbines

Abstract Industrial gas turbines like the MGT6000 are often operated as power supply or as mechanical drives. In these applications, liquid fuels like 'Diesel Fuel No.2' can be used either as main fuel or as backup fuel if natural gas is not reliably available. The MAN Gas Turbines (MGT) operate with the Advanced Can Combustion (ACC) system, which is capable of ultra-low NOx emissions for gaseous fuels. This system has been further developed to provide dry dual fuel capability. In the present paper, we describe the design and detailed experimental validation process of the liquid fuel injection, and its integration into the gas turbine package. A central lance with an integrated two-stage nozzle is employed as a liquid pilot stage, enabling ignition and start-up of the engine on liquid fuel only. The pilot stage is continuously operated, whereas the bulk of the liquid fuel is injected through the premixed combustor stage. The premixed stage comprises a set of four decentralized nozzles based on fluidic oscillator atomizers, wherein atomization of the liquid fuel is achieved through self-induced oscillations. We present results illustrating the spray, hydrodynamic, and emission performance of the injectors. Extensive testing of the burner at atmospheric and full load high-pressure conditions has been performed, before verification within full engine tests. We show the design of the fuel supply and distribution system. Finally, we discuss the integration of the dual fuel system into the standard gas turbine package of the MGT6000.

A Viscoplastic Modeling Approach for MCrAlY Protective Coatings for Gas Turbine Applications

2009 ◽  
Vol 131 (6) ◽  
Author(s):  
Roland Mücke
Keyword(s):  
Gas Turbines ◽  
Protective Coatings ◽  
Thermal Strain ◽  
Flow Characteristics ◽  
Strain Range ◽  
Substrate Material ◽  
Full Scale ◽  
Viscoplastic Material ◽  
Modeling Approach ◽  
Industrial Gas Turbines

MCrAlY coatings are applied in industrial gas turbines and aircraft engines to protect surfaces of hot gas exposed components from oxidation and corrosion at elevated temperature. Apart from oxidation resistance, coatings have to withstand cracking caused by cyclic deformation since coating cracks might propagate into the substrate material and thus limit the lifetime of the parts. In this context, the prediction of the coating maximum stress and the strain range during cyclic loading is important for the lifetime analysis of coated components. Analyzing the state of stress in the coating requires the application of viscoplastic material models. A coupled full-scale cyclic analysis of substrate and coating, however, is very expensive because of the different flow characteristics of both materials. Therefore, this paper proposes an uncoupled modeling approach, which consists of a full-scale cyclic analysis of the component without coating and a fast postprocessing procedure based on a node-by-node integration of the coating constitutive model. This paper presents different aspects of the coating viscoplastic behavior and their computational modeling. The uncoupled analysis is explained in detail and a validation of the procedure is addressed. Finally, the application of the uncoupled modeling approach to a coated turbine blade exposed to a complex engine start-up and shut-down procedure is shown. Throughout the paper bold symbols denote tensors and vectors, e.g., σ stands for the stress tensor with the components σij. The superscripts (.)S and (.)C symbolize the substrate and the coating, respectively, e.g., εthS stands for the tensor of substrate thermal strain. Further symbols are explained in the text.

The Effects of Inerts on Emissions and Performance of an Industrial Engine

1989 ◽  
Author(s):  
A. P. Rajput ◽  
P. J. Hurd ◽  
R. D. Wood
Keyword(s):  
Gas Turbines ◽  
Landfill Gas ◽  
Steam Injection ◽  
Gaseous Fuels ◽  
Thermodynamic Performance ◽  
Industrial Gas Turbines ◽  
And Performance ◽  
Emissions And Performance

Gaseous fuels such as landfill gas contain significant quantities of inerts, typically CO2 and N2. This can lead to difficulties in predicting the emission and thermodynamic performance of industrial gas turbines. An algorithm has been developed to predict emissions of NOx for known quantities of inerts and effects on performance quantified. The effect of steam injection is compared to that of inerts and a relationship established.

Dry, Low Emissions for the ‘H’ Heavy-Duty Industrial Gas Turbines: Full-Scale Combustion System Rig Test Results

2003 ◽  
Author(s):  
Geoff Myers ◽  
Dan Tegel ◽  
Markus Feigl ◽  
Fred Setzer ◽  
William Bechtel ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Full Scale ◽  
Combustion System ◽  
Heavy Duty ◽  
Test Program ◽  
Industrial Gas Turbines ◽  
Inlet Conditions

The lean, premixed DLN2.5H combustion system was designed to deliver low NOx emissions from 50% to 100% load in both the Frame 7H (60 Hz) and Frame 9H (50 Hz) heavy-duty industrial gas turbines. The H machines employ steam cooling in the gas turbine, a 23:1 pressure ratio, and are fired at 1440 C (2600 F) to deliver over-all thermal efficiency for the combined-cycle system near 60%. The DLN2.5H combustor is a modular can-type design, with 14 identical chambers used on the 9H machine, and 12 used on the smaller 7H. On a 9H combined-cycle power plant, both the gas turbine and steam turbine are fired using the 14-chamber DLN2.5H combustion system. An extensive full-scale, full-pressure rig test program developed the fuel-staged dry, low emissions combustion system over a period of more than five years. Rig testing required test stand inlet conditions of over 50 kg/s at 500 C and 28 bar, while firing at up to 1440 C, to simulate combustor operation at base load. The combustion test rig simulated gas path geometry from the discharge of the annular tri-passage diffuser through the can-type combustion liner and transition piece, to the inlet of the first stage turbine nozzle. The present paper describes the combustion system, and reports emissions performance and operability results over the gas turbine load and ambient temperature operating range, as measured during the rig test program.

Gaseous Fuels Capability of Industrial Gas Turbines

1985 ◽  
Author(s):  
W. S. Y. Hung ◽  
J. G. Meier
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Fuel Gas ◽  
Gaseous Fuels ◽  
Sanitary Landfills ◽  
Liquid Petroleum Gas ◽  
Industrial Gas Turbines ◽  
Gas Fuel ◽  
Alternate Fuels ◽  
Gas Medium

This paper describes the successful development and application of industrial gas turbines using alternate gaseous fuels. These fuels include liquid petroleum gas, medium-Btu fuels derived from biodegradation of organic matters found in sanitary landfills and liquid sewage, and ultra-low Btu fuels from oilfield fireflood operations. The analyses, mathematical modelling and rig verification performed in the development are discussed. The effects of burning these alternate fuels on the gas turbine and its combustion system are compared to those of using standard natural gas fuel. Gas turbine development required to use other alternative gaseous fuels is also assessed.

Design Features of Gas Turbine Systems Applied to Floating Production Storage and Off-Loading (FPSO) Vessels

1998 ◽  
Author(s):  
Chris Waldhelm ◽  
Peter Baron
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Oil And Gas ◽  
Cost Effective ◽  
Design Features ◽  
Industrial Gas Turbines ◽  
Alternative Means ◽  
Regulatory Bodies ◽  
Gas Market ◽  
Oil Tankers

Application of gas turbines in the off-shore oil and gas market has been successful for many years, utilizing both industrial gas turbines, as well as, aeroderivative types. Today, many operators in this market are pursuing the use of converted oil tankers and purpose-built barges — called Floating Production Storage and Off-Loading vessels (FPSO) — and semi-submersible or tension-leg platforms as alternative means of drilling for and production of oil and gas in much deeper waters than before, gaining flexibility of operation and reduced overall costs. Due to the special requirements of extreme conditions experienced on board a FPSO vessel, each application involves a considerable amount of pre-design to determine the gas turbine package required capability to satisfy needed reliability. Additionally, international and local maritime regulatory bodies and classification societies concurrence/approval generally are required to authorize vessel operation. The intent of the “Code of Construction and Equipment of Offshore Drilling Units” is to recommend design criteria, construction standards, and other safety measures in order to minimize risk to the vessels, platforms, personnel and to the environment. To incorporate these requirements into a standardized cost effective gas turbine system, this paper outlines the design features of such a package for installation on FPSO vessels.

Development and Application of Industrial Gas Turbines for Medium-Btu Gaseous Fuels

1986 ◽  
Vol 108 (1) ◽  
pp. 182-190 ◽  
Author(s):  
J. G. Meier ◽  
W. S. Y. Hung ◽  
V. M. Sood
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Combustion Process ◽  
Point Of View ◽  
Combustion System ◽  
Successful Development ◽  
Gaseous Fuels ◽  
Sanitary Landfills ◽  
Industrial Gas Turbines ◽  
Alternate Fuels

This paper describes the successful development and application of industrial gas turbines using medium-Btu gaseous fuels, including those derived from biodegradation of organic matters found in sanitary landfills and liquid sewage. The effects on the gas turbine and its combustion system of burning these alternate fuels compared to burning high-Btu fuels, along with the gas turbine development required to use alternate fuels from the point of view of combustion process, control system, gas turbine durability, maintainability and safety, are discussed.

Characterization of Metallic W-Seals for Inner to Outer Shroud Sealing in Industrial Gas Turbines

2012 ◽  
Author(s):  
Neelesh Sarawate ◽  
Chris Wolfe ◽  
Ibrahim Sezer ◽  
Ryan Ziegler ◽  
Raymond Chupp
Keyword(s):  
Gas Turbines ◽  
Weighted Average ◽  
Cost Effective ◽  
Secondary Flows ◽  
Operating Conditions ◽  
Pressure Differential ◽  
Flow Models ◽  
Operational Life ◽  
Industrial Gas Turbines ◽  
Stage 1

Sealing and clearance control are two of the most cost effective methods to reach desired goals of efficiency, power output, operational life and emission levels in turbomachinery. Metallic seals such as W seals are widely used in gas turbines to seal axial gaps between adjacent static components such as shrouds and nozzles. Often the seals are characterized in a laboratory controlled environment, and the test results are used in modeling the secondary flows. However in real operating conditions, the static components can shift relative to each other creating misalignments that result in non-uniform sealing surfaces. One such application includes sealing between the stage 1 outer and inner shrouds. The inner shrouds are often stacked with axial misalignments relative to the neighboring shrouds due to manufacturing and assembly tolerances. Characterizing the effect of shroud misalignments on the W seal leakage is reported in this article. A comprehensive test matrix is conducted to characterize W seal leakage for four different magnitudes of shroud offsets, three types of seals having varying stiffness, and two compression levels. It is observed that the W seal leakage is fairly insensitive to the compression levels and the type of seal at zero misalignments. The seal leakage increases substantially with misalignments up to four times than for a perfectly aligned condition. The seal behavior also changes with increasing offsets. The seal exhibits typical properties of a positively loaded member for small misalignments, however, the behavior resembles a loose seal for larger misalignments. For a positively loaded seal, the effective clearance of the seal increases with pressure differential, whereas in case of a loose seal, the effective clearance decreases with increasing pressure differential. The effect of misalignments must be considered when modeling the seal in the engine flow models using a weighted average of the effective clearance.

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