scholarly journals NOx Results From Two Combustors Tested on Medium BTU Coal Gas

1982 ◽  
Author(s):  
T. P. Sherlock ◽  
D. E. Carl ◽  
G. Vermes ◽  
J. Schwab ◽  
J. J. Notardonato
Keyword(s):  
Liquid Fuel ◽  
Coal Gas ◽  
Coal Gasifier ◽  
Product Gas ◽  
Gas Heating ◽  
Percent Conversion ◽  
The Rich ◽  
Inlet Conditions ◽  
Combustion Tests ◽  
Conversion Efficiencies

This paper describes the results of combustion tests of two scaled burners using actual coal gas from a 25 ton/day fluidized bed coal gasifier. The two combustor configurations studied were a ceramic-lined, staged rich/lean burner and an integral, all metal multi-annular swirl burner (MASB). The tests were conducted over a range of temperatures and pressures representative of current industrial combustion turbine inlet conditions. Tests on the rich lean burner were conducted at three levels of product gas heating values: 104, 197 and 254 Btu/Scf. Corresponding levels of NOx emissions were 5, 20 and 70 ppmv. Nitrogen was added to the fuel in the form of ammonia, and conversion efficiencies of fuel nitrogen to NOx were found to be on the order of 4 to 12 percent, which is somewhat lower than the 14 to 18 percent conversion efficiency when SRC-II liquid fuel was used. The MASB was tested only on medium Btu gas (220 to 270 Btu/Scf), and produced approximately 80 ppmv NOx at rated engine conditions. It is concluded that both burners operated similarly on actual coal gas and ERBS fuel, and that all heating values tested can be successfully burned in current machines.

scholarly journals Boundary Layer Control by Means of Strong Injection

1984 ◽  
Vol 51 (1) ◽  
pp. 27-34 ◽  
Author(s):  
R.-J. Yang ◽  
M. Holt
Keyword(s):  
Pipe Flow ◽  
Pipe Wall ◽  
Flow System ◽  
Wall Jet ◽  
Direction Parallel ◽  
Coal Gas ◽  
Coal Gasifier ◽  
Gas Products ◽  
Strong Injection ◽  
Layer Control

The gas mixture produced by coal gasifier contains components that have serious corrosive effects on the walls of the pipe flow system. To reduce these, a non-corrosive gas is injected into the stream of the coal gas products, in a direction parallel to the pipe wall. The interaction between the injected stream and the original pipe flow is investigated analytically and is an example of the so-called Wall Jet Problem.

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.

Detailed Research on Rich-Lean Type Single Sector Combustor for Small Aircraft Engine Tested Under Practical Conditions Up to 3MPa

2012 ◽  
Author(s):  
Mitsumasa Makida ◽  
Hideshi Yamada ◽  
Kazuo Shimodaira
Keyword(s):  
Experimental Research ◽  
Aircraft Engine ◽  
Emission Characteristics ◽  
Nox Emissions ◽  
Additional Test ◽  
Lean Combustion ◽  
Test Conditions ◽  
The Rich ◽  
Combustion Tests ◽  
Small Aircraft

In the TechCLEAN project of JAXA, experimental research has been conducted to develop a combustor for a small aircraft engine. The combustor was tuned to show the behavior of the Rich-Lean combustion through tests under atmospheric and practical conditions. Finally, through full annular combustion experiments under practical conditions, the combustor was tuned to reduce NOx emissions to almost 40% of the ICAO CAEP4 standard, also sustaining low CO and THC emissions. To investigate the performance of the combustor in detail, parametric experiments were conducted with single-sector combustors under additional test conditions in addition to design conditions of the target engine. Also the performance as a combustor for higher-efficient aircraft engine is examined by increasing inlet air pressure and temperature up to 3MPa and 825K in combustion tests. Obtained results of emission characteristics are discussed in this report.

scholarly journals Experimental Evaluation of Simplified IGCC

1984 ◽  
Author(s):  
M. W. Horner ◽  
J. C. Corman
Keyword(s):  
Gas Turbine ◽  
Pilot Scale ◽  
Combined Cycle ◽  
Experimental Program ◽  
Inlet Temperature ◽  
Fuel System ◽  
Fuel Gas ◽  
Capital Costs ◽  
Coal Gas ◽  
Coal Gasifier

Integrated gasification combined cycle (IGCC) power plants offer the opportunity to burn coal in an environmentally sound manner at a competitive cost of output energy. Advanced simplified IGCC systems have been identified which offer reduced fuel system capital costs and complexity as well as improved thermal efficiency of coal to fuel conversion. These systems, however, must utilize hot gas cleanup devices to remove particulates, alkali metals, and sulfur to permit utilization of the product fuel gas in a gas turbine. Technology and component development are underway to prepare the hot fuel gas cleanup and gas turbine systems for subsequent integration and verification testing at pilot scale. An experimental testing program is underway to address fuel system and gas turbine components technology for a simplified IGCC configuration. Gas turbine nozzle sectors have been adapted for installation in a turbine simulator for development testing. A low-Btu gas combustor installed upstream of the nozzle sectors is utilized to burn a hot coal gas. Modifications have been made to an existing pilot scale coal gasifier to deliver 1000°F low-Btu coal gas to the gas turbine combustor after partial cleanup by a hot cyclone to remove particulate matter carried over from the coal gasifier. The results from this experimental program will resolve technical issues related to corrosion, deposition and erosion phenomena related to fuel quality, turbine inlet temperature, and nozzle metal surface temperature.

Alternative Fuels: Burner Concepts and Emission Characteristics of a Silo Combustor

1982 ◽  
Author(s):  
W. Krockow ◽  
H. Schabbehard
Keyword(s):  
Residence Time ◽  
Alternative Fuels ◽  
Liquid Fuels ◽  
Emission Characteristics ◽  
Test Results ◽  
Coal Gas ◽  
The Rich ◽  
Burning Coal ◽  
Kinetic Calculations ◽  
The Impact

As the design philosophy of a silo combustor differs largely from the better known one of smaller can type combustors, the paper describes the impact of alternative fuels on the burner concepts and emission characteristics of the silo combustor. Some published influences of a higher C/H-ratio on wall temperatures and smoke emission could not be observed. The large volume of the silo combustor offers the possibility of burning coal derived gases with heat values as low as 1800 kJ/kg. Nitrogenous liquid fuels need a rich burning first combustion stage with a long residence time. Calculations which closely agree with latest published test results show the pronounced effect of residence time to the rich burn quick quench concept. This becomes even more distinct in the case of a low BTU coal gas containing NH3 or HCN resulting in unrealistic large combustor volumes. In addition, a general graph based on kinetic calculations shows the expected NOx increase or decrease of any kind of CO, H2 and inert concentration in a coal gas related to the NOx result of methane in the same combustor.

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.

Comparison of Liquid Fuel/Air Mixing and NOx Emissions for a Tangential Entry Nozzle

1994 ◽  
Author(s):  
Timothy S. Snyder ◽  
Thomas J. Rosfjord ◽  
John B. McVey ◽  
Louis M. Chiappetta
Keyword(s):  
Droplet Size ◽  
Liquid Fuel ◽  
Fuel Injection ◽  
Experimental Program ◽  
Spatial Density ◽  
Main Body ◽  
Initial Droplet ◽  
Combustion Tests ◽  
Initial Droplet Size ◽  
Injection Location

An experimental program was conducted to develop a technique for designing a dry low NOx liquid fuel injection configuration for a tangential entry lean-premixed fuel nozzle. Calculations were performed to predict the effect of liquid fuel injection location, orifice size and spacing, and initial droplet size on the vaporized fuel/air mixture uniformity exiting the highly-swirled premixing nozzle. Combustion tests were conducted at pressures ranging from 10–18 atm, and inlet temperatures ranging from 650–730 K, for the different liquid fuel injection schemes analyzed from the mixing study. Liquid fuel injection configurations that were predicted to give the best fuel/air distribution generated the lowest levels of NOx. The calculated fuel/air uniformity was a weak function of the spatial density of liquid fuel injection sites and the method of injecting the liquid fuel. The injection location and initial droplet size have the greatest impacts on fuel/air uniformity. The analysis indicated that 40 micron diameter droplets mix adequately while larger droplets (80 micron) are centrifuged out of the main body of the flow and produce locally high fuel/air ratios. The NOx levels achieved for the best liquid fuel injection configuration approached those obtained for a well premixed gas fuel configuration using the same tangential entry nozzle.

Results and Experience From Operation and Testing of ALSTOM’s 30 MW GT10C Gas Turbine

2003 ◽  
Author(s):  
Anders Hellberg ◽  
Georg Norden ◽  
Mats Andersson ◽  
Thomas Widgren ◽  
Christer Hjalmarsson ◽  
...  
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Liquid Fuel ◽  
Engine Performance ◽  
Liquid Fuels ◽  
Critical Parameters ◽  
Test Rig ◽  
Load Range ◽  
Performance And Emissions ◽  
Inlet Conditions

ALSTOM’s new gas turbine, the GT10C, is a 30 MW industrial gas turbine for mechanical drive and power generation, which has been upgraded from the 25 MW GT10B. The thermal efficiency of the new gas turbine is 37.3% at ISO inlet conditions with no losses. The GT10C features a dual-fuel dry low emission gas turbine, with emissions values of 15 ppm NOx on gaseous fuel and 42 ppm NOX on liquid fuel (also dry). The GT10C was first started and operated on load in November 2001 and the test program is ongoing until the fall of 2002. The program covers a complete package test, including gas turbine, auxiliaries and control system, to ensure package availability. For the tests, a new test rig has been built in Finspong, Sweden, for testing on both natural gas and liquid fuels. The tests have been very successful, achieving the product targets, for example below 15 ppm NOx, without combustor pulsations. This paper discusses operation experience from the test rig, where the engine has been tested on both natural gas and liquid fuel over the whole load range. The engine has been equipped with over 1200 measuring points, covering the complete gas turbine. All critical parameters have been carefully verified in the test, such as turbine blade temperature and stresses, combustor temperatures and dynamics and engine performance. Results from the tests and measurements will be discussed in this paper. Performance and emissions will also be evaluated.

Simulation of Coal Conversion Reactor Environments

CORROSION ◽  
1980 ◽  
Vol 36 (4) ◽  
pp. 167-173 ◽  
Author(s):  
RICHARD A. COOKE ◽  
OWEN F. DEVEREUX
Keyword(s):  
Gas Phase ◽  
Equilibrium Constants ◽  
Multiple Equilibrium ◽  
Carbon Phase ◽  
Coal Gas ◽  
Coal Gasifier ◽  
Molten Sodium ◽  
Partial Pressures ◽  
Activity Ratios ◽  
Salt Phase

Abstract Two models simulating the coal gasifier environment are described; Model 1 comprises coal gas components and a molten sodium salt phase, while Model 2 also includes a solid carbon phase. The use of equilibrium constants to compute the equilibrium state of an open system and the occurrence of multiple equilibrium states are detailed. Representative computations pertaining to the two models are shown in which dependent partial pressures and activity ratios are computed as function of temperature, total pressure, and the partial pressures of hydrogen, carbon monoxide, and hydrogen sulfide. The dominant anion in the liquid phase is mapped as a function of equilibrium gas phase composition.

scholarly journals Experimental research of liquid-fueled continuously rotating detonation chamber

Shock Waves ◽  
2021 ◽  
Author(s):  
P. Wolański ◽  
W. Balicki ◽  
W. Perkowski ◽  
A. Bilar
Keyword(s):  
Liquid Fuel ◽  
Fuel Injection ◽  
Liquid Fuels ◽  
Turbine Engines ◽  
Practical Application ◽  
Propulsion Systems ◽  
Hot Air ◽  
Mixture Preparation ◽  
The Rich ◽  
Rotating Detonation

AbstractResearch on the application of liquid fuels to continuously rotating detonation was conducted. A new method of mixture preparation was proposed. A special system of liquid fuel injection was designed and tested which is based on injecting into the detonation chamber a preheated liquid fuel partially mixed with hot air at conditions higher than the rich flammability limit. The specially selected conditions allow all liquid fuel to evaporate in the supply system but prevent it from ignition before entering the detonation chamber. Experiments were conducted for two different liquid fuels, extraction gasoline and Jet-A fuel. Research was carried out for different equivalence ratios, and in all tested conditions detonation was achieved. The new tested method of liquid fuel preparation and injection into a cylindrical detonation chamber opens a way of application of liquid fuels to engines which utilize continuously rotating detonation and thus prepares the way for practical application of detonative combustion to turbine engines and jet propulsion systems.

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