The Performance of the Low NOx Aero Gas Turbine Combustor Under High Pressure

2001 ◽  
Author(s):  
Takashi Ikezaki ◽  
Jun Hosoi ◽  
Hidemi Toh ◽  
Toshiro Fujimori ◽  
Motohide Murayama ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Nox Reduction ◽  
Gas Turbine Combustor ◽  
High Pressure And Temperature ◽  
Auto Ignition ◽  
Annular Combustor ◽  
Fuel Nozzle ◽  
Combustion Tests ◽  
Emission Index

We have developed a new fuel staged combustor, which consists of diffusion flame pilot burners and lean premixing prevaporizing main burners and is therefore called a multiple fuel nozzle type low NOx gas turbine combustor. The goal for NOx reductions was set to 70 to 80% compared with conventional gas turbine combustors. Combustion tests for a section of the annular combustor have been performed for pressures P3 up to 2.9Mpa and temperatures T3 up to 823K with kerosene. As the results, even under high pressure and temperature condition, stable combustion without the problem of auto-ignition or flashback could be achieved. NOx emission index is 13 [g/kg,fuel] which is equivalent to more than 70% NOx reduction. The liner wall temperature is lower than the durability limit. The dependency of NOx emissions on pressure and temperature for this combustor are reported.

scholarly journals Effect of Water Injection for NOx Reduction With Synthetic Liquid Fuels Containing High Fuel-Bound Nitrogen in a Gas Turbine Combustor

1981 ◽  
Author(s):  
P. R. Mulik ◽  
P. P. Singh ◽  
A. Cohn
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Nox Reduction ◽  
Water Injection ◽  
Liquid Fuels ◽  
Gas Turbine Combustor ◽  
Synthetic Liquid Fuel ◽  
Effect Of Water ◽  
Combustion Tests ◽  
No Emissions

A total of five combustion tests utilizing water injection for control of NO, emissions have been conducted on three types of coal-derived liquid (CDL) fuels from the H-Coal and SRC II processes along with a shale-derived liquid (SDL) fuel supplied by the Radian Corporation. Actual testing was performed in a 0.14 m diameter gas-turbine-type combustor. For comparative purposes, each run with a synthetic liquid fuel was preceded by a baseline run utilizing No. 2 distillate oil. The effectiveness of water injection was found to decrease as the fuel-bound nitrogen (FBN) content of the synthetic liquids increased.

scholarly journals Wall Temperature Measurements in a Full Scale Gas Turbine Combustor Test Rig With Fiber Coupled Phosphor Thermometry

2020 ◽  
Author(s):  
Patrick Nau ◽  
Simon Görs ◽  
Christoph Arndt ◽  
Benjamin Witzel ◽  
Torsten Endres
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Wall Temperature ◽  
Full Scale ◽  
Temperature Measurements ◽  
Test Facility ◽  
Fiber Optic Probe ◽  
Gas Turbine Combustor ◽  
Phosphor Thermometry ◽  
Combustion Tests

Abstract Wall temperature measurements with fiber coupled online phosphor thermometry were, for the first time, successfully performed in a full scale H-class Siemens gas turbine combustor. Online wall temperatures were obtained during high-pressure combustion tests up to 8 bar at the Siemens CEC test facility. Since optical access to the combustion chamber with fibers being able to provide high laser energies is extremely challenging, we developed a custom-built measurement system, consisting of a water-cooled fiber optic probe and a mobile measurement container. A suitable combination of chemical binder and thermographic phosphor was identified for temperatures up to 1800 K on combustor walls coated with a thermal barrier coating (TBC). To our knowledge these are the first measurements reported with fiber coupled online phosphor thermometry in a full scale high-pressure gas turbine combustor. Details of the setup and the measurement procedures will be presented. The measured signals were influenced by strong background emissions, probably from CO2* chemiluminescence. Strategies for correcting background-emissions and data evaluation procedures are discussed. The presented measurement technique enables detailed study of combustor wall temperatures and using this information an optimization of the gas turbine cooling design.

Hydrogen Blending Into Ansaldo Energia AE94.3A Gas Turbine: High Pressure Tests, Field Experience and Modelling Considerations

2021 ◽  
Author(s):  
A. Ciani ◽  
L. Tay-Wo-Chong ◽  
A. Amato ◽  
E. Bertolotto ◽  
G. Spataro
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Power Plants ◽  
Flame Structure ◽  
Flux Ratio ◽  
Fuel Blends ◽  
Pressure Tests ◽  
Fuel Staging ◽  
Combustion Tests ◽  
The Impact

Abstract Fuel flexibility in gas turbine development has become increasingly important and modern engines need to cope with a broad variety of fuels. The target to operate power plants with hydrogen-based fuels and low emissions will be of paramount importance in a future focusing on electric power decarbonization. Ansaldo Energia AE94.3A engine acquired broad experience with operation of various natural gas and hydrogen fuel blends, starting in 2006 in the Brindisi (Italy) power plant. Based on the exhaustive experience acquired in the field, this paper describes the latest advancements characterizing the operation of the AE94.3A burner with high pressure combustion tests adding hydrogen blends ranging from 0 to 40% in volume. The interpretation of the test results is supported by reactive and non-reactive simulations describing the effects of varying fuel reactivity on the flame structure as well as the impact of fuel / air momentum flux ratio on the fuel / air interaction and fuel distribution in the combustion chamber. As expected, increasing amounts of hydrogen in the fuel are also associated with higher amounts of NOx production, however this effect could be countered by optimization of the fuel staging strategy, based on the mentioned CFD considerations and feedback from high pressure tests.

An Experimental Study on Modeling of Fuel Atomization for Simulating the Idle Regime of a Gas Turbine Combustor by Atmospheric Testing

1997 ◽  
Author(s):  
Yeoung Min Han ◽  
Min Soo Yoon ◽  
Woo Seok Seol ◽  
Dae Sung Lee ◽  
Victor I. Yagodkin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Diagnostic Methods ◽  
Fuel Spray ◽  
Main Stage ◽  
Gas Turbine Combustor ◽  
Spray Characteristics ◽  
Fuel Atomization ◽  
Fuel Nozzle ◽  
Loading Parameter ◽  
The Cost

An experimental investigation is carried out on modeling of fuel atomization for the purpose of simulating the idle regime of a gas turbine combustor through atmospheric testing. If the simulation is successfully applied, it will significantly reduce the cost of testing. The simulation must sustain nearly the same fuel spray characteristics and the same aerodynamics at the exit of the frontal device. Air assisting through the main stage of a dual orifice fuel nozzle is employed to match the fuel spray characteristics. Optical diagnostic methods including flow visualization and Adaptive Phase/Doppler Velocimetry are used for the investigation of spray characteristics. Once the fuel spray characteristics are matched by air assisting, the combustor characteristics may then be matched by maintaining the loading parameter constant. The possibility of modeling with air assisting is shown and appropriate conditions for air assisting are found.

Kinetics Modeling on NOx Emissions of a Syngas Turbine Combustor Using RQL Combustion Method

2019 ◽  
Author(s):  
Haoyang Liu ◽  
Wenkai Qian ◽  
Min Zhu ◽  
Suhui Li
Keyword(s):  
Gas Turbine ◽  
Residence Time ◽  
Air Flow ◽  
Nox Reduction ◽  
Outlet Temperature ◽  
Nox Emissions ◽  
Gas Turbine Combustor ◽  
Kinetics Modeling ◽  
The Rich ◽  
Nox Control

Abstract To avoid flashback issues of the high-H2 syngas fuel, current syngas turbines usually use non-premixed combustors, which have high NOx emissions. A promising solution to this dilemma is RQL (rich-burn, quick-mix, lean-burn) combustion, which not only reduces NOx emissions, but also mitigates flashback. This paper presents a kinetics modeling study on NOx emissions of a syngas-fueled gas turbine combustor using RQL architecture. The combustor was simulated with a chemical reactor network model in CHEMKIN-PRO software. The combustion and NOx formation reactions were modeled using a detailed kinetics mechanism that was developed for syngas. Impacts of combustor design/operating parameters on NOx emissions were systematically investigated, including combustor outlet temperature, rich/lean air flow split and residence time split. The mixing effects in both the rich-burn zone and the quick-mix zone were also investigated. Results show that for an RQL combustor, the NOx emissions initially decrease and then increase with combustor outlet temperature. The leading parameters for NOx control are temperature-dependent. At typical modern gas turbine combustor operating temperatures (e.g., < 1890 K), the air flow split is the most effective parameter for NOx control, followed by the mixing at the rich-burn zone. However, as the combustor outlet temperature increases, the impacts of air flow split and mixing in the rich-burn zone on NOx reduction become less pronounced, whereas both the residence time split and the mixing in the quick-mix zone become important.

scholarly journals Conversion of Liquid to Gaseous Fuel for Prevaporised Premixed Combustion in Gas Turbines

1997 ◽  
Author(s):  
Y. Wang ◽  
L. Reh ◽  
D. Pennell ◽  
D. Winkler ◽  
K. Döbbeling
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Liquid Fuel ◽  
Fuel Injection ◽  
Premixed Combustion ◽  
Fuel Oil ◽  
Injection System ◽  
Nox Emissions ◽  
Combustion Tests

Stationary gas turbines for power generation are increasingly being equipped with low emission burners. By applying lean premixed combustion techniques for gaseous fuels both NOx and CO emissions can be reduced to extremely low levels (NOx emissions <25vppm, CO emissions <10vppm). Likewise, if analogous premix techniques can be applied to liquid fuels (diesel oil, Oil No.2, etc.) in gas-fired burners, similar low level emissions when burning oils are possible. For gas turbines which operate with liquid fuel or in dual fuel operation, VPL (Vaporised Premixed Lean)-combustion is essential for obtaining minimal NOx-emissions. An option is to vaporise the liquid fuel in a separate fuel vaporiser and subsequently supply the fuel vapour to the natural gas fuel injection system; this has not been investigated for gas turbine combustion in the past. This paper presents experimental results of atmospheric and high-pressure combustion tests using research premix burners running on vaporised liquid fuel. The following processes were investigated: • evaporation and partial decomposition of the liquid fuel (Oil No.2); • utilisation of low pressure exhaust gases to externally heat the high pressure fuel vaporiser; • operation of ABB premix-burners (EV burners) with vaporised Oil No.2; • combustion characteristics at pressures up to 25bar. Atmospheric VPL-combustion tests using Oil No.2 in ABB EV-burners under simulated gas turbine conditions have successfully produced emissions of NOx below 20vppm and of CO below 10vppm (corrected to 15% O2). 5vppm of these NOx values result from fuel bound nitrogen. Little dependence of these emissions on combustion pressure bas been observed. The techniques employed also ensured combustion with a stable non luminous (blue) flame during transition from gaseous to vaporised fuel. Additionally, no soot accumulation was detectable during combustion.

Endoscopic Chemiluminescence Measurements as a Robust Experimental Tool in High-Pressure Gas Turbine Combustion Tests

2014 ◽  
Author(s):  
Simon Goers ◽  
Benjamin Witzel ◽  
Johannes Heinze ◽  
Guido Stockhausen ◽  
Jaap van Kampen ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Measurement Techniques ◽  
Pressure Oscillations ◽  
Combustion Dynamics ◽  
Pressure Transducers ◽  
Experimental Tool ◽  
Gas Turbine Combustion ◽  
Combustion Tests ◽  
The Impact

The development process for gas turbine combustion systems includes single-burner high-pressure combustion tests as an important validation step. In these tests the performance of a combustor is investigated at realistic gas turbine conditions. Measurement techniques that are typically used in these tests include mass flow meters, thermocouples, pressure transducers, and probes for exhaust-gas composition measurements. These measurement techniques, however, do not provide direct information of the flame behavior. Chemiluminescence measurements have proven to being a valuable and robust technique to close this gap [1,2]. This paper summarizes the results of chemiluminescence measurements performed at Siemens full-scale high-pressure single-burner combustion test rigs at the German Aerospace Center (DLR) in Cologne, Germany. To minimize the impact of the measurement system on the experiment, the optical access to the test rigs was provided by a water-cooled endoscopic probe. The probe was located in a side-wall downstream of the burner, viewing upstream towards the burner outlet. The probe was successfully operated up to full engine pressure and flame temperatures of approximately 1900 K. For the detection of the chemiluminescence signal different approaches were applied: • Spectral analyses of the chemiluminescence signal were done by using an USB spectrometer. • For flame imaging up to two intensified CCD cameras were applied. In front of the cameras various combinations of optical filters were installed to selectively record the respective chemiluminescent species (OH*, CH*, CO2*). • For studies with special focus on combustion dynamics an intensified high-speed CMOS camera was used. High-repetition-rate measurements were used for identifying the shapes of flame modes. • Acoustic pressure oscillations inside the combustion chamber were recorded by pressure transducers simultaneously to the camera images. This allows the pressure oscillations to be correlated with flame fluctuations during post-processing [3,4]. Generally, the robustness of endoscopic chemiluminescence measurements was successfully demonstrated in numerous tests at realistic gas turbine conditions. The applied imaging setups provided new information about the connection between the flame position and NOx emissions as well as the correlation of flame fluctuations and pressure oscillations. Hence, they have become a valuable experimental tool to improve the evaluation and understanding of the combustor performance. Future work will focus on further improvement of quantitative evaluations by compensation of line-of-sight image integration, reabsorption of OH* by OH, and beam steering.

scholarly journals Test Result of Low NOx Catalytic Combustor for Gas Turbine

1993 ◽  
Author(s):  
Y. Ozawa ◽  
J. Hirano ◽  
M. Sato ◽  
M. Saiga ◽  
S. Watanabe
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Combustion Method ◽  
Combustion Efficiency ◽  
Gas Temperature ◽  
Gas Turbine Combustor ◽  
Combustion Gas ◽  
Low Nox Combustion ◽  
Catalytic Combustor ◽  
Combustion Tests

Catalytic combustion is an ultra low NOx combustion method, so it is expected that this method will be applied to gas turbine combustor. However, it is difficult to develop catalytic combustor because catalytic reliability at high temperature is still insufficient. To overcome this difficulty, we designed a catalytic combustor in which premixed combustion was combined. By this device, it is possible to obtain combustion gas at a combustion temperature of 1300°C while keeping the catalytic temperature below 1000°C. After performing preliminary tests using LPG, we designed two types of combustors for natural gas with a capacity equivalent to 1 combustor used in a 20MW–class multi–can type gas turbine. Combustion tests were conducted at atmospheric pressure using natural gas. As a result, it was confirmed that a combustor in which catalytic combustor segments were arranged alternately with premixing nozzles could achieve low NOx and high combustion efficiency in the range from 1000°C to 1300°C of the combustor exit gas temperature.

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