scholarly journals Testing of a Full Scale, Low Emissions, Ceramic Gas Turbine Combustor

1997 ◽  
Author(s):  
K. Smith ◽  
A. Fahme
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Combustion Efficiency ◽  
Full Scale ◽  
Significant Deterioration ◽  
Lean Premixed Combustion ◽  
Fuel Injectors ◽  
Primary Zone ◽  
Test Engine ◽  
Cooling Air

The design and development testing of a full scale, low emissions, ceramic combustor for a 5500 HP industrial gas turbine are described. The combustor was developed under a joint program conducted by the U.S. DOE and Solar Turbines. The ceramic combustor is designed to replace the production Centaur 50S SoLoNOx burner which uses lean-premixed combustion to limit NOx and CO to 25 and 50 ppm, respectively. Both the ceramic and production combustors are annular in shape and employ twelve premixing, natural gas fuel injectors. The ceramic combustor design effort involved the integration of two CFCC cylinders (76.2 cm [30 in.] and 35.56 cm [14 in.] diameters) into the combustor primary zone. The ceramic combustor was evaluated at Solar in full scale test rigs and a test engine. Performance of the combustor was excellent with high combustion efficiency and extremely low NOx and CO emissions. The hot walls of the ceramic combustor played a significant role in reducing CO emissions. This suggests that liner cooling air injected through the metal production liner contributes to CO emissions by reaction quenching at the liner walls. It appears that ceramics can serve to improve combustion efficiency near the combustor lean limit which, in turn, would allow further reductions in NOx emissions. Approximately 50 hours of operation have been accumulated using the ceramic combustor. No significant deterioration in the CFCC liners has been observed. A 4000 hour field test of the combustion system is planned to begin in 1997 as a durability assessment.

Development of a Natural Gas-Fired, Ultra-Low NOx Can Combustor for an 800 KW Gas Turbine

1991 ◽  
Author(s):  
K. O. Smith ◽  
A. C. Holsapple ◽  
H. K. Mak ◽  
L. Watkins
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Premixed Combustion ◽  
Experimental Results ◽  
Nox Emissions ◽  
Variable Geometry ◽  
Lean Premixed Combustion ◽  
Full Load ◽  
Primary Zone ◽  
Lean Premixed

The experimental results from the rig testing of an ultra-low NOx, natural gas-fired combustor for an 800 to 1000 kw gas turbine are presented. The combustor employed lean-premixed combustion to reduce NOx emissions and variable geometry to extend the range over which low emissions were obtained. Testing was conducted using natural gas and methanol. Testing at combustor pressures up to 6 atmospheres showed that ultra-low NOx emissions could be achieved from full load down to approximately 70% load through the combination of lean-premixed combustion and variable primary zone airflow.

On-Site Emissions and Fuel Consumption Measurement to Compare Locomotive Fuel Injector Performance

2006 ◽  
Author(s):  
W. Scott Wayne ◽  
Ryan A. Barnett ◽  
Jeffrey M. Cutright ◽  
Ted E. Stewart
Keyword(s):  
West Virginia ◽  
Fuel Consumption ◽  
Alternative Fuels ◽  
Engine Performance ◽  
Combustion Efficiency ◽  
Fuel Injector ◽  
West Virginia University ◽  
Test Procedures ◽  
Fuel Injectors ◽  
Locomotive Engine

As part of the Norfolk-Southern Railroad’s on-going investigation into fuel consumption reductions for their fleet of 3000 locomotives, the Center for Alternative Fuels, Engines and Emissions at West Virginia University conducted on-site locomotive engine performance and emissions measurements to characterize the performance, fuel consumption and emissions associated with fuel injectors from two injector suppliers. Emissions and fuel consumption were measured using the West Virginia University Transportable Locomotive Emissions Testing Laboratory, which was set up at the Norfolk-Southern Heavy Repair Facility in Roanoke, Virginia. The tests were conducted to evaluate potential emissions and fuel consumption differences between two fuel injector suppliers using an EMD GP38-2 locomotive equipped with a 2100 hp (1566 kW), 16-cylinder, EMD 16-645E engine. The test locomotive engine was freshly overhauled and certified to the EPA locomotive Tier 0 emissions standards. Emissions and fuel consumption measurements were conducted according to the Federal Test Procedures defined in the Code of Federal Regulations 40CFR Part 92 Subpart B [1]. The engine was first tested in the “as overhauled” configuration with the OEM fuel injectors to establish the baseline emissions and fuel consumption. The baseline FTP results confirmed that this locomotive was in compliance with the Federal Tier 0 emissions standards. The OEM specification fuel injectors were replaced with “Fuel Saver” injectors designed and manufactured by an aftermarket injector supplier referred to in this paper as Supplier B. The Supplier B injectors reduced fuel consumption on the average of 2–4% for each notch, except for Notch 4 and Low Idle. However, the Supplier B injectors increased the NOx levels by 20–30% for almost every notch, which is an expected result due to the improved combustion efficiency.

scholarly journals Experimental Evaluation of a Low Emissions, Variable Geometry, Small Gas Turbine Combustor

1990 ◽  
Author(s):  
K. O. Smith ◽  
M. H. Samii ◽  
H. K. Mak
Keyword(s):  
Gas Turbine ◽  
Experimental Evaluation ◽  
Premixed Combustion ◽  
Nox Emissions ◽  
Variable Geometry ◽  
Test Results ◽  
Gas Turbine Combustor ◽  
Lean Premixed Combustion ◽  
Primary Zone ◽  
Lean Premixed

The results of an on-engine evaluation of an ultra-low NOx, natural gas-fired combustor for a 200 kW gas turbine are presented. The combustor evaluated used lean-premixed combustion to reduce NOx emissions and variable geometry to extend the range over which low emissions were obtained. Test results showed that ultra-low NOx emissions could be achieved from full load down to approximately 50% load through the combination of lean-premixed combustion and variable primary zone airflow.

Influence of Swirl and Primary Zone Airflow Rate on the Emissions and Performance of a Liquid-Fueled Gas Turbine Combustor

2019 ◽  
Vol 141 (6) ◽  
Author(s):  
Parneeth Lokini ◽  
Dinesh Kumar Roshan ◽  
Abhijit Kushari
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Combustible Mixture ◽  
Airflow Rate ◽  
Nox Emissions ◽  
Swirl Number ◽  
Primary Zone ◽  
Air Mixing ◽  
Efficient Combustion ◽  
And Performance

This paper presents the results of an experimental study on the influence of swirl number (S) and primary zone airflow rate on the temperature, emission indices of the pollutants, and combustion efficiency in an atmospheric pressure liquid-fueled gas turbine (GT) combustor, equipped with a swirling jet air blast atomizer and operated with Jet A1 fuel. Experiments were conducted at three primary zone air flow rates and three swirl numbers (0.49, 0.86, and 1.32). For all the cases, it was found that the NOx emissions were very low (< 2 g/kg of fuel). At all the swirl numbers, an increase in primary zone airflow led to a nonmonotonous variation in CO while minimally affecting the NOx emissions. However, increase in the swirl number generated relatively higher NOx and lower CO owing to higher temperature resulting from efficient combustion caused by a superior fuel–air mixing. Also, the unburnt hydrocarbons (UHC) was quite high at S = 0.49 because of the unmixedness of fuel and air, and zero at S = 0.86 and 1.32. The combustion efficiency was very low (around 60%) at S = 0.49 while almost 100% at S = 0.86 and 1.32. The study conducted demonstrates a significant dependence of emissions and GT performance on the swirl number governed by the convective time scales and the residence time of the combustible mixture in the combustion zone.

scholarly journals Development of the Nissan YTP-12 Gas Turbine Engine

1976 ◽  
Author(s):  
Y. Sumi ◽  
S. Yamazaki ◽  
K. Kinoshita
Keyword(s):  
Gas Turbine ◽  
Mechanical Design ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Durability Test ◽  
Turbine Engine ◽  
Component Test ◽  
Test Engine ◽  
Engine Development ◽  
Mechanical Arrangement

This paper describes the later progress of the Nissan YTP-12 gas turbine engine development. The mechanical design and the progress in its development are reviewed. The discussion includes mechanical arrangement, material, fuel control, major problems encountered and their solution. Component test, engine performance and durability test, and vehicle installation test are discussed briefly.

Measurements Inside a Bluff-Body Stabilized Gas Turbine Combustor for Application of Pressurized Biomass Derived Low Calorific Value Fuel Gas and Comparison of the Results: Part 2

2006 ◽  
Author(s):  
Marco van der Wel ◽  
Wiebren de Jong ◽  
Hartmut Spliethoff
Keyword(s):  
Gas Turbine ◽  
Bluff Body ◽  
Calorific Value ◽  
Combustion Efficiency ◽  
Medium Size ◽  
Gas Turbine Combustor ◽  
Fuel Gas ◽  
Primary Zone ◽  
Secondary Air ◽  
Comparison Of The Results

In our previous paper [Van der Wel (2005)] the main results about combustion efficiency and emissions have been presented of experiments with a medium size (TUD) combustor of 1.5 MWth operated on low calorific value (LCV) fuel gas with heating values (HHV) ranging from 1.88 to 4.64 MJ/m3n (50 to 120 Btu/scf). In the current paper the experiments are presented where the amount of primary and secondary air are varied in order to examine the effects of stoichiometry on the combustors performance and these results are compared with a previously tested downscaled typhoon combustor from ALSTOM. Also, results are presented with respect to traversing measurements behind the primary zone of the TUD combustor. It was found that the NH3 to NO conversion decreases at increasing pressure and that higher concentrations of methane in the fuel result in higher ammonia to NO conversions. Also it was observed that the swirling typhoon combustor seemed to have less problems achieving lower ammonia conversions than the bluff body stabilized TUD combustor.

scholarly journals Developments in Air Cooling of Gas Turbine Vanes and Blades

1983 ◽  
Author(s):  
Darryl E. Metzger
Keyword(s):  
Gas Turbine ◽  
Research Work ◽  
Engine Performance ◽  
Detailed Knowledge ◽  
Air Cooling ◽  
Turbine Engine ◽  
Engine Cooling ◽  
History Of ◽  
Effective Use ◽  
Cooling Air

Over the history of gas turbine engine development, improvements in engine performance are closely tied to increases in the level of tolerable turbine inlet temperatures. The ability to operate at increasingly high temperatures has been the result of both improvements in materials capability and advances in the art of cooling the hot section components. For propulsion engines and their derivatives the cooling medium is air supplied from the compressor stages, requiring an expense of engine power. The hot section airfoils, particularly the first stage vanes and blades, consume a significant fraction of the total engine cooling air. Designers are continuously faced with the task of making more effective use of the coolant to improve either performance or durability or both. The design process requires detailed knowledge of heat transfer and flow friction characteristics for present and candidate future cooling schemes. Typical current cooling schemes and associated research work directed to future improved designs are discussed.

scholarly journals An Advanced Development of a Second-Generation Dry, Low-NOx Combustor for 1.5MW Gas Turbine

1996 ◽  
Author(s):  
Shin-ichi Kajita ◽  
Shin-ichi Ohga ◽  
Masahiro Ogata ◽  
Satoru Itaka ◽  
Jun-ichi Kitajima ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Second Generation ◽  
Nox Reduction ◽  
Combustion Efficiency ◽  
Combustion System ◽  
Endurance Test ◽  
Industrial Gas Turbine ◽  
Cooling Air ◽  
Cycle Endurance ◽  
Advanced Development

Advanced development of a second-generation dry, low-NOx combustor for KHI’s 1.5MW industrial gas turbine, M1A-13A, is described. In this advanced development, efforts were made mainly to improve combustion efficiency in addition to NOx reduction experimentally. The combustion liner was extended to increase combustion volume, and supplemental burners were installed downstream of multiple main burners to broaden low-NOx operation range. In consequence of the optimization of the fuel allotment, air/fuel ratio at each burner, cooling air, and so on, the engine showed NOx emissions under 15 ppm (15% O2), and a combustion efficiency more than 99.5% over the range between 75% and 100% load. Finally, by means of a 300-hour operation at full load and a 500-cycle endurance test, the total reliability of this combustion system was ensured.

Low-Emissions Gas Turbine Combustor Development for Regional-Class Aircraft

2000 ◽  
Author(s):  
J. Zelina ◽  
P. F. Penko
Keyword(s):  
Gas Turbine ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Test Results ◽  
Fuel Injectors ◽  
Primary Zone ◽  
Performance And Emissions ◽  
Rectangular Area

Sector-rig test results of four combustor configurations for medium-sized, gas-turbine engines are presented. The sector test section consists of a three-injector combustor cross-section, unrolled to a rectangular area, and simulating about a sixty-eight degree section of the combustor. Performance and emissions data are presented for four design-of-experiment (DOE) combinations of 1) air swirlers, 2) fuel injectors, and 3) primary-zone lengths. Emission concentrations from gas sampling are given for NOx, CO, and UHC as a function of inlet temperature, pressure, and overall fuel air ratio. NOx production as a function of inlet temperature, pressure, stoichiometry, and residence time are presented. The trade-off between NOx and CO is given over a range of operating conditions for each sector configuration.

Development of a Dry Low NOx Combustor for 2MW Class Gas Turbine

1996 ◽  
Author(s):  
J. Hosoi ◽  
T. Watanabe ◽  
H. Toh ◽  
M. Mori ◽  
H. Sato ◽  
...  
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Film Cooling ◽  
Combustion Efficiency ◽  
Premixed Combustion ◽  
Lean Premixed Combustion ◽  
Wide Region ◽  
Lean Premixed

Development of a dry low NOx combustor for 2MW class gas turbine is described, which has been co-conducted by Ishikawajima-Harima Heavy Industries Co., Ltd. and Tokyo Gas Co., Ltd. from 1994. This combustor is characterized by three stage, lean premixed combustion with coaxial burners operated by simple control system and non-film cooling, from which low NOx and high combustion efficiency within the wide region of load can be obtained. Component rig tests indicated NOx ≒10ppm (at 16% O2), combustion efficiency η c >99.8% could be obtained over load more than 50%.

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