Full-Engine Field Test: An Approach to Improve the Gas Turbine Combustion System

1988 ◽  
Vol 110 (4) ◽  
pp. 677-685
Author(s):  
M. Gianola
Keyword(s):  
Experimental Data ◽  
Temperature Distribution ◽  
Gas Turbine ◽  
Field Test ◽  
Test Bench ◽  
Fuel Oil ◽  
Ignition Process ◽  
Exit Plane ◽  
Combustion System ◽  
Oil And Natural Gas

For purposes of both final verification and optimization of TG 20 and TG 50 combustion systems, test programs have been carried out directly on full engines operating in the field, as well as in the test bench. These programs were carried out in two separate phases: the first one directed to determine the behavior at load by means of experimental data acquisition, including temperature distribution on the combustor exit plane for different burner arrangements, and the second one directed to optimize the ignition process and the acceleration sequence. This paper, after a brief description of the instrumentation used for each test, reports the most significant results burning both fuel oil and natural gas. Moreover, some peculiar operational problems are mentioned, along with their diagnosis and the corrections applied to the combustion system to solve them.

Acoustic Control of Dilution-Air Mixing in a Gas Turbine Combustor

1982 ◽  
Author(s):  
P. J. Vermeulen ◽  
J. Odgers ◽  
V. Ramesh
Keyword(s):  
Temperature Distribution ◽  
Temperature Profile ◽  
Gas Turbine ◽  
Exit Plane ◽  
Gas Turbine Combustor ◽  
Acoustic Control ◽  
Air Mixing ◽  
Air Flows ◽  
Plane Temperature ◽  
Load Conditions

A small combustor of normal design employing acoustic control of the dilution-air flows has been successfully tested up to “half-load” conditions. It has been shown that this technique can be used to selectively and progressively control the exit plane temperature distribution, and the ability to trim the temperature profile has been convincingly demonstrated. The acoustic driver power requirements were minimal indicating that driver power at “full-load” will not be excessive. The nature of the acoustically modulated dilution-air flows has been clearly establish to the design of combustors such that a desired exit plane temperature distribution may be achieved.

Combustion System Performance and Field Test Results of the MS7001F Gas Turbine

1993 ◽  
Vol 115 (3) ◽  
pp. 537-546 ◽  
Author(s):  
J. P. Claeys ◽  
K. M. Elward ◽  
W. J. Mick ◽  
R. A. Symonds
Keyword(s):  
Gas Turbine ◽  
Field Test ◽  
System Performance ◽  
Mechanical Performance ◽  
Steam Injection ◽  
Test Results ◽  
Combustion System ◽  
Dynamic Activity ◽  
Unburned Hydrocarbons ◽  
Nox Control

This paper presents the results of the combustion system test of the MS7001F installed at the Virginia Power Chesterfield station. Tests of water and steam injection for NOx control were performed. Results of emissions, combustor dynamics, and combustor hardware performance are presented. Emissions test results include NOx, CO, unburned hydrocarbons, VOC, and formaldehyde levels. Combustor dynamic activity over a range of diluent injection ratios, and the performance of an actively cooled transition duct are also discussed. Combustion system mechanical performance is described following the first combustion system inspection.

Field Test Validation of the DLN2.5H Combustion System on the 9H Gas Turbine at Baglan Bay Power Station

2005 ◽  
Author(s):  
Markus Feigl ◽  
Fred Setzer ◽  
Rebecca Feigl-Varela ◽  
Geoff Myers ◽  
Bryan Sweet
Keyword(s):  
Gas Turbine ◽  
Field Test ◽  
Test Performance ◽  
Gas Turbines ◽  
Combined Cycle ◽  
Combustion System ◽  
Test Program ◽  
Power Station ◽  
Industrial Gas Turbines ◽  
Characterization Test

The lean, premixed H combustion system was targeted to deliver low NOx and CO emissions from 50% to 100% combined cycle load in both the Frame 7H (60 Hz) and Frame 9H (50 Hz) heavy-duty industrial gas turbines. The H System™ is the first gas turbine combined-cycle technology capable of achieving 60% thermal efficiency. The present paper describes field test performance of the combustion system during the launch and operation of the initial MS9001H installation at Baglan Bay power station near Port Talbot, Wales. The 480 MW 9H combined cycle, fired using the 14-chamber DLN2.5H combustion system, was comprehensively evaluated during the gas turbine Characterization Test program over a period of several months in late 2002 and 2003. Results are reported for exhaust emissions, combustor component durability, operability, and other key combustion system performance parameters over the full gas turbine operating range. The present paper also describes the operability of the H combustion system throughout a rigorous validation of the power plant system, including National Grid Council testing, load rejections, and other key system transients.

Design Parameters for an Aircraft Engine Exit Plane Particle Sampling System

2010 ◽  
Vol 133 (2) ◽  
Author(s):  
Hsi-Wu Wong ◽  
Zhenhong Yu ◽  
Michael T. Timko ◽  
Scott C. Herndon ◽  
Elena de la Rosa Blanco ◽  
...  
Keyword(s):  
Experimental Data ◽  
System Design ◽  
Gas Turbine ◽  
Black Carbon ◽  
Particle Formation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Exit Plane ◽  
Sampling System ◽  
Sampling Line

The experimental data and numerical modeling were utilized to investigate the effects of exhaust sampling parameters on the measurements of particulate matter (PM) emitted at the exit plane of gas-turbine engines. The results provide guidance for sampling system design and operation. Engine power level is the most critical factor that influences the size and quantity of black carbon soot particles emitted from gas-turbine engines and must be considered in sampling system design. The results of this investigation indicate that the available soot surface area significantly affects the amount of volatile gases that can condense onto soot particles. During exhaust particle measurements, a dilution gas is typically added to the sampled exhaust stream to suppress volatile particle formation in the sampling line. Modeling results indicate that the dilution gas should be introduced upstream before a critical location in the sampling line that corresponds to the onset of particle formation microphysics. Also, the dilution gas should be dry for maximum nucleation suppression. In most aircraft PM emissions measurements, the probe-rake systems are water cooled and the sampling line may be heated. Modeling results suggest that the water cooling of the probe tip should be limited to avoid overcooling the sampling line wall temperature and, thus, minimize additional particle formation in the sampling line. The experimental data show that heating the sampling lines will decrease black carbon and sulfate PM mass and increase organic PM mass reaching the instruments. Sampling line transmission losses may prevent some of the particles emitted at the engine exit plane from reaching the instruments, especially particles that are smaller in size. Modeling results suggest that homogeneous nucleation can occur in the engine exit plane sampling line. If newly nucleated particles, typically smaller than 10 nm, are indeed formed in the sampling line, sampling line particle losses provide a possible explanation, in addition to the application of dry diluent, that they are generally not observed in the PM emissions measurements.

Conjugate Heat Transfer Simulation of a Radially Cooled Gas Turbine Vane

2004 ◽  
Author(s):  
Bruno Facchini ◽  
Andrea Magi ◽  
Alberto Scotti Del Greco
Keyword(s):  
Heat Transfer ◽  
Experimental Data ◽  
Temperature Distribution ◽  
Gas Turbine ◽  
Conjugate Heat Transfer ◽  
Circular Cross Section ◽  
External Temperature ◽  
Turbine Vane ◽  
Heat Transfer Simulation ◽  
The Impact

A 3D conjugate heat transfer simulation of a radially cooled gas turbine vane has been performed using STAR-CD™ code and the metal temperature distribution of the blade has been obtained. The study focused on the linear NASA-C3X cascade, for which experimental data are available; the blade is internally cooled by air through ten radially oriented circular cross section channels. According to the chosen approach, boundary conditions for the conjugate analysis were specified only at the inlet and outlet planes and on the openings of the internal cooling channels: neither temperature distribution nor heat flux profile were assigned along the walls. Static pressure, external temperature and heat transfer coefficient distributions along the vane were compared with experimental data. In addition, in order to asses the impact of transition on heat transfer profile, just the external flow (supposed fully turbulent in the conjugate approach) was separately simulated with TRAF code too and the behaviour of the transitional boundary layer has been analyzed and discussed. Loading distributions were found to be in good agreement with experiments for both conjugate and non conjugate approaches, but, since both pressure and suction side exhibit a typical transitional behavior, HTC profiles obtained without taking into account transition severely overestimate experimental data especially near the leading edge. Results confirm the significant role of transition in predicting heat transfer and, therefore, vane temperature field when a conjugate analysis is performed.

Development of a Micro Gas Turbine Combustion System for Fuel Oil: CFD-Lay-Out and Combustion Tests

2009 ◽  
Author(s):  
I. Schmitz ◽  
V. Scherer
Keyword(s):  
Gas Turbine ◽  
Development Process ◽  
Fuel Oil ◽  
Combustion System ◽  
Micro Gas Turbine ◽  
Operation Conditions ◽  
Oil Pump ◽  
Droplet Sizes ◽  
Combustion Tests ◽  
Careful Design

The current paper presents the development of a lean premixed prevaporized (LPP) combustion system for a micro gas turbine. A commercial spill return atomizer and a standard fuel oil pump as used in domestic burner applications were specified for the fuel supply system. The relatively large droplet sizes generated by this kind of atomizer system require careful design of the evaporation section of the combustion system. The usage of a LPP combustion concept implies the risk of self ignition and flash back. To avoid both, the knowledge of the ignition delay time and the flame speed of fuel oil are essential for the design of the combustion system. The paper describes the development process of the combustion system and presents experimental results for different geometries and operation conditions.

Feasibility of Utilizing a Bio-Mass Derived Fuel for Industrial Gas Turbine Applications

1995 ◽  
Author(s):  
R. G. Andrews ◽  
P. C. Patnaik ◽  
J. W. Michniewicz ◽  
L. J. Jankowski ◽  
V. I. Romanov ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Operating Conditions ◽  
Fuel Oil ◽  
Combustion System ◽  
Test Vehicle ◽  
Heating Value ◽  
Turbine Engine ◽  
Standard Operating ◽  
Industrial Gas Turbine

This paper describes a development program aimed at determining the technical feasibility of utilizing a bio-mass derived fuel in an industrial gas turbine engine. The fuel addressed is a flammable bio-fuel oil derived from wood waste through flash pyrolysis. The fuel has a heating value of approximately 18 MJ/kg, a density of 1.2 kg/l and specialized wet filtration techniques are used to minimize the particulate matter in the fuel. The turbine engine selected, as the test vehicle, is a 2.5 MW class-GT2500 engine designed and built by Mashproekt in the Ukraine. The standard operating conditions and layout of this engine provide flexibility in optimization of the combustion system to accept lower than conventional grade fuels. The characteristics of the fuel, the fuel handling system, and the considerations with respect to igniting and maintaining combustion with a fuel of this nature are discussed.

Massive Steam Injection on an MS6001B Gas Turbine in Cogeneration Service

1992 ◽  
Author(s):  
Kevin M. Elward ◽  
David A. Flodman ◽  
Richard A. Symonds
Keyword(s):  
Gas Turbine ◽  
Field Test ◽  
Laboratory Testing ◽  
Dynamic Pressure ◽  
Steam Injection ◽  
Steam Flow ◽  
Combustion System ◽  
Gas Fuel ◽  
Nox Control

A recent field test has completed the qualification of the MS6001B combustion system for operation on gas fuel with steam injection for NOx control to 25 ppmvd. Recently, dry operation on gas fuel at 25 ppmvd has been achieved on the MS6001. To meet the immediate need for running at the 25 ppmvd NOx level, increased steam injection was investigated. Laboratory testing on a single MS6001 combustor indicated the potential for achieving NOx levels as low as 25 ppmvd through the use of steam injection. This paper describes the lab testing and the field test of the MS6001B, and includes data on emissions, steam flow requirements, and dynamic pressure levels. The MS6001B is now available at 25 ppmvd NOx with steam injection on gas wherever this level is required. This system provides an easy retrofit to those gas fired, steam injected units where installation of the dry 25 ppmvd NOx system is not immediately feasible.

scholarly journals Combustion System Performance and Field Test Results of the MS7001F Gas Turbine

1992 ◽  
Author(s):  
James P. Claeys ◽  
Kevin M. Elward ◽  
Warren J. Mick ◽  
Richard A. Symonds
Keyword(s):  
Gas Turbine ◽  
Field Test ◽  
System Performance ◽  
Mechanical Performance ◽  
Steam Injection ◽  
Test Results ◽  
Combustion System ◽  
Dynamic Activity ◽  
Unburned Hydrocarbons ◽  
Nox Control

This paper presents the results of the combustion system test of the MS7001F installed at the Virginia Power Chesterfield station. Tests of water and steam injection for NOx control were performed. Results of emissions, combustor dynamics, and combustor hardware performance are presented. Emissions test results include NOx, CO, unburned hydrocarbons, VOC and formaldehyde levels. Combustor dynamic activity over a range of diluent injection ratios, and the performance of an actively cooled transition duct are also discussed. Combustion system mechanical performance is described following the first combustion system inspection.

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