Development of a Dry Ultra-Low NOx Double Swirler Staged Gas Turbine Combustor

1998 ◽  
Vol 120 (1) ◽  
pp. 41-47 ◽  
Author(s):  
H. Sato ◽  
M. Mori ◽  
T. Nakamura
Keyword(s):  
Gas Turbine ◽  
Gas Flow ◽  
Combustion Efficiency ◽  
Nox Emission ◽  
Superior Performance ◽  
Operating Pressure ◽  
Gas Turbine Combustor ◽  
Fuel Gas ◽  
Combustion Tests ◽  
Low Nox Emission

This paper describes the development of an ultra-low NOx gas turbine combustor for cogeneration systems. The combustor, called a double swirler staged combustor, utilizes three-staged premixed combustion for low NOx emission. The unique feature of the combustor is its tertiary premix nozzles located downstream of the double swirler premixing nozzles around the combustor liner. Engine output is controlled by simply varying the fuel gas flow, and therefore employs no complex variable geometries for airflow control. Atmospheric combustion tests have demonstrated the superior performance of the combustor. NOx level is maintained at less than 3 ppm (O2 = 15 percent) over the range of engine output between 50 and 100 percent. Assuming the general relationship that NOx emission is proportional to the square root of operating pressure, the NOx level is estimated at less than 9 ppm (O2 = 15 percent) at the actual pressure of 0.91 MPa (abs.). Atmospheric tests have also shown high combustion efficiency; more than 99.9 percent over the range of engine output between 60 and 100 percent. Emissions of CO and UHC are maintained at 0 and 1 ppm (O2 = 15 percent), respectively, at the full engine load.

scholarly journals Development of a Dry Ultra Low NOx Double Swirler Staged Gas Turbine Combustor

1996 ◽  
Author(s):  
Hiroshi Sato ◽  
Masaaki Mori
Keyword(s):  
Gas Turbine ◽  
Gas Flow ◽  
Combustion Efficiency ◽  
Nox Emission ◽  
Superior Performance ◽  
Operating Pressure ◽  
Gas Turbine Combustor ◽  
Fuel Gas ◽  
Combustion Tests ◽  
Low Nox Emission

This paper describes the development of an ultra-low NOx gas turbine combustor for cogeneration systems. The combustor, called a double swirler staged combustor, utilizes three-staged premixed combustion for low NOx emission. The unique feature of the combustor is its tertiary premix nozzles located downstream of the double swirler premixing nozzles around the combustor liner. Engine output is controlled by simply varying the fuel gas flow, and therefore employs no complex variable geometries for air flow control. Atmospheric combustion tests have demonstrated the superior performance of the combustor. NOx level is maintained at less than 3 ppm (O2=15%) over the range of engine output between 50% and 100%. Assuming the general relationship that NOx emission is proportional to the square root of operating pressure, the NOx level is estimated at less than 9 ppm (O2=15%) at the actual pressure of 0.91 MPa (abs.). Atmospheric tests have also shown high combustion efficiency; more than 99.9% over the range of engine output between 60% and 100%. Emissions of CO and UHC are maintained at 0 and 1 ppm (O2=15%), respectively, at the full engine load.

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.

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.

Performance of a Dry Low NOx Gas Turbine Combustor With an Improved Innovative Fuel Supply Concept

2004 ◽  
Author(s):  
Tsutomu Wakabayashi ◽  
Koji Moriya ◽  
Shonosuke Koga ◽  
Kazuo Shimodaira ◽  
Yoji Kurosawa ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Pressure Loss ◽  
Combustion Efficiency ◽  
Gaseous Fuel ◽  
Gas Turbine Combustor ◽  
Fuel Distribution ◽  
Fuel Supply ◽  
Fuel Jet ◽  
Pressurized Combustion ◽  
Combustion Tests

This paper describes the combustion performance of a dry low-NOx gas turbine combustor designed with an innovative fuel supply concept using gaseous fuel. This concept uses spontaneous fuel distribution achieved by an interaction between the gaseous fuel jet and the airflow. Previously, we proved that fuel distribution based on the innovative fuel supply concept actually occurred according to the load by means of pressurized combustion tests using a prototype combustor. However, NOx was not low enough at high loads, and combustion efficiency was not high at medium and low loads. Further, the pressure loss of the combustor was high. Therefore, the prototype combustor was improved from the viewpoint of NOx, combustion efficiency and combustor pressure loss. This paper describes the detailed structure of the improved combustors and the results of the pressurized combustion experiments.

Gas Turbine Combined Cycle With CO2-Capture Using Auto-Thermal Reforming of Natural Gas

2000 ◽  
Author(s):  
Thormod Andersen ◽  
Hanne M. Kvamsdal ◽  
Olav Bolland
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Process Integration ◽  
Combined Cycle ◽  
Co2 Removal ◽  
Gas Turbine Combustor ◽  
Chemical Absorption ◽  
Fuel Gas ◽  
The Impact ◽  
Water Gas

A concept for capturing and sequestering CO2 from a natural gas fired combined cycle power plant is presented. The present approach is to decarbonise the fuel prior to combustion by reforming natural gas, producing a hydrogen-rich fuel. The reforming process consists of an air-blown pressurised auto-thermal reformer that produces a gas containing H2, CO and a small fraction of CH4 as combustible components. The gas is then led through a water gas shift reactor, where the equilibrium of CO and H2O is shifted towards CO2 and H2. The CO2 is then captured from the resulting gas by chemical absorption. The gas turbine of this system is then fed with a fuel gas containing approximately 50% H2. In order to achieve acceptable level of fuel-to-electricity conversion efficiency, this kind of process is attractive because of the possibility of process integration between the combined cycle and the reforming process. A comparison is made between a “standard” combined cycle and the current process with CO2-removal. This study also comprise an investigation of using a lower pressure level in the reforming section than in the gas turbine combustor and the impact of reduced steam/carbon ratio in the main reformer. The impact on gas turbine operation because of massive air bleed and the use of a hydrogen rich fuel is discussed.

Combustion Characteristics of Small Size Gas Turbine Combustor Fueled by Biomass Gas Employing Flameless Combustion

2007 ◽  
Author(s):  
Masato Hiramatsu ◽  
Yoshifumi Nakashima ◽  
Sadamasa Adachi ◽  
Yudai Yamasaki ◽  
Shigehiko Kaneko
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Combustion Characteristics ◽  
Operating Conditions ◽  
Nox Emissions ◽  
Gas Turbine Combustor ◽  
Flameless Combustion ◽  
Engine Exhaust ◽  
Micro Gas Turbine

One approach to achieving 99% combustion efficiency (C.E.) and 10 ppmV or lower NOx (at 15%O2) in a micro gas turbine (MGT) combustor fueled by biomass gas at a variety of operating conditions is with the use of flameless combustion (FLC). This paper compares experimentally obtained results and CHEMKIN analysis conducted for the developed combustor. As a result, increase the number of stage of FLC combustion enlarges the MGT operation range with low-NOx emissions and high-C.E. The composition of fuel has a small effect on the characteristics of ignition in FLC. In addition, NOx in the engine exhaust is reduced by higher levels of CO2 in the fuel.

High Temperature Stability of MGCs Gas Turbine Components in Air and Combustion Gas Flow Environments

2004 ◽  
Author(s):  
Narihito Nakagawa ◽  
Hideki Ohtsubo ◽  
Kohji Shibata ◽  
Atsuyuki Mitani ◽  
Kazutoshi Shimizu ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Gas Flow ◽  
Temperature Stability ◽  
High Temperature Strength ◽  
High Temperature Stability ◽  
Combustion Gas ◽  
Air Atmosphere ◽  
Low Nox Emission ◽  
Very High

Melt growth composites (MGCs) have a unique microstructure, in which continuous networks of single-crystal phases interpenetrate without grain boundaries. Therefore, the MGCs have excellent high-temperature strength characteristics, creep resistance, oxidation resistance and thermal stability in an air atmosphere at very high temperature. To achieve ultra-high thermal efficiency and low NOx emission for gas turbine systems, non-cooled turbine nozzle vanes and heat shield panels of combustor liners has been fabricated on an experimental basis. These components are thermally stable after heat treatment at 1700°C for 1000 hours in an air atmosphere. In addition, we have just started the exposure tests to evaluate the influence of combustion gas flow environment on MGCs.

Combustion of Coal/Water Mixtures With Thermal Preconditioning

1987 ◽  
Vol 109 (3) ◽  
pp. 313-318 ◽  
Author(s):  
M. Novack ◽  
G. Roffe ◽  
G. Miller
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Experimental Program ◽  
Water Mixture ◽  
Gas Turbine Combustor ◽  
Hydrocarbon Gases ◽  
Sampling Probe ◽  
Stable Flame ◽  
Thermal Preconditioning ◽  
Gaseous Form

Thermal preconditioning is a process in which coal/water mixtures are vaporized to produce coal/steam suspensions, and then superheated to allow the coal to devolatilize producing suspensions of char particles in hydrocarbon gases and steam. This final product of the process can be injected without atomization, and burned directly in a gas turbine combustor. This paper reports on the results of an experimental program in which thermally preconditioned coal/water mixture was successfully burned with a stable flame in a gas turbine combustor test rig. Tests were performed at a mixture flowrate of 300 lb/hr and combustor pressure of 8 atm. The coal/water mixture was thermally preconditioned and injected into the combustor over a temperature range from 350°F to 600°F, and combustion air was supplied at between 600°F to 725°F. Test durations varied between 10 and 20 min. Major results of the combustion testing were that: A stable flame was maintained over a wide equivalence ratio range, between φ = 2.2 (rich) and 0.2 (lean); and combustion efficiency of over 99 percent was achieved when the mixture was preconditioned to 600°F and the combustion air preheated to 725°F. Measurements of ash particulates, captured in the exhaust sampling probe located 20 in. from the injector face, show typical sizes collected to be about 1 μm, with agglomerates of these particulates to be not more than 8 μm. The original mean coal particle size for these tests, prior to preconditioning, was 25 μm. Results of additional tests showed that one third of the sulfur contained in the solids of a coal/water mixture with 3 percent sulfur was evolved in gaseous form (under mild thermolized conditions) mainly as H2S with the remainder as light mercaptans.

Analysis of air-staged combustion of NH3/CH4 mixture with low NOx emission at gas turbine conditions in model combustors

Fuel ◽  
2019 ◽  
Vol 237 ◽  
pp. 50-59 ◽  
Author(s):  
Shan Li ◽  
Shanshan Zhang ◽  
Hua Zhou ◽  
Zhuyin Ren
Keyword(s):  
Gas Turbine ◽  
Nox Emission ◽  
Staged Combustion ◽  
Low Nox Emission
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