scholarly journals A Water Quenched Low NOx Coal Slurry Combustor for Industrial Gas Turbines

1989 ◽  
Author(s):  
C. Wilkes ◽  
M. K. Razdan ◽  
C. B. Santanam
Keyword(s):  
Gas Turbines ◽  
Calorific Value ◽  
Combustion Model ◽  
Stable Operation ◽  
Coal Slurry ◽  
Oxides Of Nitrogen ◽  
Turbine Engine ◽  
Bench Scale ◽  
Industrial Gas Turbines ◽  
The Rich

A 1.8 kgs/sec (4 lbs/sec) bench-scale rich-quench-lean combustor has been successfully developed to burn micronized coal-water slurry (CWS) mixtures with 50% solids loading. Water quenching is used to freeze and shatter slag particles leaving the rich zone which are trapped and removed from the hot gas stream in a cyclone separator. Rich zone carbon burnout efficiencies in excess of 99% have been measured experimentally and are in good agreement with two-dimensional (2-D) coal combustion model predictions. Stable operation in the rich zone on 100% CWS at design conditions has been achieved. The low calorific value gas (125 to 445 Kcal/scm, 14 to 50 Btu/scf) produced in the quench zone, auto ignited in the lean zone at all conditions and self-sustained combustion was maintained without the need for auxiliary fuel. Low measured values of carbon monoxide (CO) and oxides of nitrogen (NOx) concentrations in the exhaust gases have demonstrated the ability of the combustor to control emissions to well within acceptable levels. The bench-scale data provides a technology base for the design of a 15 kgs/sec (33 lbs/sec) combustor that will be used for testing of an advanced coal-fueled gas turbine engine.

Performance Deterioration in Industrial Gas Turbines

1992 ◽  
Vol 114 (2) ◽  
pp. 161-168 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

Performance Deterioration in Industrial Gas Turbines

1991 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

GSP, a Generic Object-Oriented Gas Turbine Simulation Environment

2000 ◽  
Author(s):  
Wilfried P. J. Visser ◽  
Michael J. Broomhead
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Object Oriented ◽  
Control Logic ◽  
Turbine Engine ◽  
Industrial Gas Turbines ◽  
On Line ◽  
Turboshaft Engine

NLR’s primary tool for gas turbine engine performance analysis is the ‘Gas turbine Simulation Program’ (GSP), a component based modeling environment. GSP’s flexible object-oriented architecture allows steady-state and transient simulation of any gas turbine configuration using a user-friendly drag&drop interface with on-line help running under Windows95/98/NT. GSP has been used for a variety of applications such as various types of off-design performance analysis, emission calculations, control system design and diagnostics of both aircraft and industrial gas turbines. More advanced applications include analysis of recuperated turboshaft engine performance, lift-fan STOVL propulsion systems, control logic validation and analysis of thermal load calculation for hot section life consumption modeling. In this paper the GSP modeling system and object-oriented architecture are described. Examples of applications for both aircraft and industrial gas turbine performance analysis are presented.

Development and F-Class Industrial Gas Turbine Engine Testing of Smart Components With Direct-Write Embedded Sensors and High Temperature Wireless Telemetry

2008 ◽  
Author(s):  
David Mitchell ◽  
Anand Kulkarni ◽  
Edward Roesch ◽  
Ramesh Subramanian ◽  
Andrew Burns ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Condition Based Maintenance ◽  
Direct Write ◽  
Turbine Engine ◽  
Wireless Telemetry ◽  
Industrial Gas Turbines ◽  
Engine Testing ◽  
Industrial Gas Turbine

The potential for savings provided to worldwide operators of industrial gas turbines, by transitioning from the current standard of interval-based maintenance to condition-based maintenance may be in the tens of millions of dollars per year. Knowledge of the historical and current condition of life-limiting components will enable more efficient use of industrial gas turbine resources via increased operational flexibility, with less risk of unplanned outages as a result of off-parameter operations. To date, it has been impossible to apply true condition-based maintenance to industrial gas turbines because the extremely harsh operating conditions in the heart of a gas turbine preclude using the necessary advanced sensor systems to monitor the machine’s condition continuously. The U.S. Department of Commerce’s National Institute of Standards and Technology – Advanced Technology Program (NIST-ATP) awarded the Joint Venture team of Siemens Power Generation, Inc. and MesoScribe Technologies, Inc. a four-year, $5.4 million program in November, 2004, titled Conformal, Direct-Write-Technology-Enabled, Wireless, Smart Turbine Components. The target was to develop a potentially industry-changing technology to build smart, self-aware engine components that incorporate embedded, harsh-environment-capable sensors and high temperature capable wireless telemetry systems for continuously monitoring component condition in both the compressor and turbine sections. The approach involves several difficult engineering challenges, including the need to embed sensors on complex shapes, such as turbine blades, embedding wireless telemetry systems in regions with temperatures that preclude the use of conventional silicon-based electronics, protecting both sensors and wireless devices from the extreme temperatures and environments of an operating gas turbine, and successfully transmitting the sensor information from an environment very hostile to wireless signals. The program included full-scale, F-class industrial gas turbine engine test demonstrations with smart components in both the compressor and turbine sections. The results of the development program and engine testing to date will be discussed.

On-Design and Off-Design Performance Analysis of a Gas Turbine Combined Cycle Using the Exergy Method

2000 ◽  
Author(s):  
Alcides Codeceira Neto ◽  
Pericles Pilidis
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Exergy Analysis ◽  
Pressure Ratio ◽  
Calorific Value ◽  
Combined Cycle ◽  
Exergy Destruction ◽  
Turbine Engine ◽  
Design Point

The present paper describes an on-design and an off-design performance study of gas turbine combined cycle based power plants. The exergy analysis has been carried out along with the performance assessment, considering the overall plant exergetic efficiency and the exergy destruction in the various components of the plant. The exergy method highlights irreversibility within the plant components, and it is of particular interest in this investigation. A computational analysis has been carried out to investigate the effects of compressor pressure ratio and gas turbine entry temperature on the thermodynamic performance of combined gas / steam power cycles. The exergy analysis has been performed for on-design point calculations, considering single shaft gas turbines with different compressor pressure ratios and turbine entry temperatures. Nearly 100 MW shaft power gas turbine engines burning natural gas fuel have been selected in this study. The off-design calculations have been performed for one of the gas turbines selected from the on-design point studies. For this particular gas turbine engine, fuel has been changed from natural gas to a low calorific value fuel gas originated from the gasification of wood. The exergy analysis indicates that maximum exergy is destroyed in the combustor, in the case of combined gas / steam cycles burning natural gas. For these studies on-design point, the exergy destruction in the combustor is found to decrease with increasing compressor pressure ratio to an optimum value and with increasing turbine entry temperature. In the off-design case the gas turbine engine is burning low calorific value fuel originated from the gasification of wood. The maximum exergy destruction occurs in the gasification process, followed by the combustion process in the gas turbine.

Low NOx Combustion Systems for Burning Heavy Residual Fuels and High-Fuel-Bound Nitrogen Fuels

1982 ◽  
Vol 104 (2) ◽  
pp. 377-385 ◽  
Author(s):  
D. J. White ◽  
A. Batakis ◽  
R. T. LeCren ◽  
H. G. Yacobucci
Keyword(s):  
Gas Turbines ◽  
Department Of Energy ◽  
Technical Program ◽  
Turbine Engine ◽  
Industrial Gas Turbines ◽  
Low Nox Combustion ◽  
Thermal Nox ◽  
Nox Control ◽  
Industrial Gas Turbine ◽  
And Control

The work described in this paper is a part of the Department of Energy/Lewis Research Center (DOE/LeRC) “Advanced Conversion Technology” (ACT) project. The program is a multiple contract effort with funding provided by the Department of Energy and technical program management provided by NASA LeRC. The increasingly critical situation concerning the world’s petroleum supply necessitates the investigation of alternate fuels for use in industrial gas turbines. Environmentally acceptable operation with minimally processed petroleum based heavy residual and coal derived synthetic fuels requires advanced combustor technology. The technology described in this paper was developed under the DOE/NASA Low NOx Heavy Fuel Combustor Concept Program (Contract DEN3-145). Novel combustor concepts were designed for dry reduction of thermal NOx, control of NOx from fuels containing high levels of organic nitrogen, and control of smoke from low hydrogen content fuels. These combustor concepts were tested by burning a wide variety of fuels including a middle distillate (ERBS), a petroleum based heavy residual, a coal derived synthetic (SRC-II), and various ratios of blends of these fuels which included nitrogen doping with pyridine. The results of these tests show promise that low NOx emissions and high efficiencies can be obtained over most of the operating range of a typical industrial gas turbine engine.

Environmental Performance of Industrial Gas Turbines

1974 ◽  
Author(s):  
R. H. Johnson ◽  
Colin Wilkes
Keyword(s):  
Air Pollution ◽  
Carbon Monoxide ◽  
Environmental Performance ◽  
Gas Turbines ◽  
Hydrocarbon Fuel ◽  
Industrial Society ◽  
Oxides Of Nitrogen ◽  
The World ◽  
Industrial Gas Turbines ◽  
Power Needs

At this point in time, everyone is “for the environment” and this is true the world world over because the atmosphere is shared by peoples of all nations. Air pollution from hydrocarbon fuel combustion, both worldwide and local, is discussed by reviewing known measurements of contaminants. Application of gas turbines by industry is one way to provide power needs for attaining and maintaining an industrial society. Environmental performance of industrial gas turbines with respect to exhaust emissions and environmental impact is presented for oxides of nitrogen, hydrocarbons, carbon monoxide, particulate matter and visible smoke. Results of recent abatement efforts are also presented together with estimates of potential improvements to show the place of the industrial combustion turbine in a world with growing concern for environmental improvement.

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.

Cycle Optimisation Using an Advanced, Real Engine Performance Prediction Model

2002 ◽  
Author(s):  
Miles Coppinger ◽  
Graham Cox ◽  
John Hannis ◽  
Nigel Cox
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Integer Number ◽  
Turbine Engine ◽  
Engine Model ◽  
Engine Design ◽  
Industrial Gas Turbines ◽  
High Degree ◽  
Technology Level

A whole gas-turbine engine model has been developed incorporating all of the key turbomachinery aerothermal relationships. The aim of the model has been to predict trends in gas-turbine performance with a high degree of confidence that they reflect real engine design limitations. Simple cycles, recuperated, inter-cooled, and inter-cooled recuperated cycles can be assessed across a wide of range of operating parameters. The model is spreadsheet-based with additional macro programming. The major part of it is concerned with establishing representative overall turbine characteristics. A non-integer number of stages is determined as a function of technology level inputs. Individual stage geometry features are derived allowing the calculation of the coolant requirements and efficiencies. The results of various studies are presented for a number of cycle types. The resulting trends are believed to be sensible because of the realistic turbine features. Confidence in the method is established by the modelling of a number of existing industrial gas turbines.

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