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

2005 ◽  
Author(s):  
Marco van der Wel ◽  
Wiebren de Jong ◽  
Hartmut Spliethoff
Keyword(s):  
Gas Turbine ◽  
Bluff Body ◽  
Calorific Value ◽  
Medium Size ◽  
Wood Pellets ◽  
Gas Turbine Combustor ◽  
Fuel Gas ◽  
Miscanthus Giganteus ◽  
Primary Zone ◽  
Comparison Of The Results

A medium size gas turbine combustor of 1.5 MW of Delft University (TUD) has been tested to combust low calorific value (LCV) fuel gas. The LCV gas was obtained from pressurized gasification of wood pellets class A, miscanthus giganteus and brown coal and was cleaned from its particulates by high temperature ceramic filters of β-cordierite. Stable combustion of (biomass derived) low calorific value fuel gas with heating values (LHV) between 1.64 and 4.48 MJ/m3n (50 to 120 Btu/scf) was accomplished due to high fuel gas temperatures ranging from 845 to 1099 K. Main species (O2, CO2,) and minor species (Ar, CH4, H2, CO, NO) were measured in the exhaust and by a traversing probe after the primary zone of the combustor. The water and nitrogen contents in the exhaust were calculated from the element balances. The results are compared with a previously tested combustor of ALSTOM Power of the RQL type.

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 Biomass/Coal Derived Gas Utilization in a Gas Turbine Combustor

1998 ◽  
Author(s):  
P. D. J. Hoppesteyn ◽  
J. Andries ◽  
K. R. G. Hein
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Calorific Value ◽  
Two Dimensional ◽  
Dimensional Model ◽  
Gas Turbine Combustor ◽  
Cylindrical Chamber ◽  
Fuel Gas ◽  
Gas Utilization ◽  
Two Dimensional Model

Low calorific value fuel gas, obtained by pressurized fluidized bed gasification of coal/biomass mixtures, is combusted at 0.8 MPa with air or oxygen in a vertical cylindrical chamber (D = 0.28 m, L = 2.0 m). The fuel (T = 1060 K) and oxydizer (air at 350 K, oxygen at 460 K) are injected coaxially, resulting in an essentially axissymmetric flow pattern. Particles have been removed from the fuel gas stream by a cyclone, mounted between the gasifier and the combustor. A two-dimensional model, implemented in the CFD code FLUENT was developed for the calculation of temperatures, flow patterns and species concentrations throughout the combustor. The calculated results are compared with experimental data for two low calorific value fuel gas compositions and two oxidizer compositions at two axial combustor locations (X/L = 0.175 and X/L = 1). The results appear to justify further investigation of the applicability of the model to low calorific value fuel gas fired gas turbine combustors.

Improvement of the Outlet Temperature Distribution of a Dual-Fuel Gas Turbine Combustor by a Simplified CFD Model

2012 ◽  
Author(s):  
Paolo Gobbato ◽  
Andrea Lazzaretto ◽  
Massimo Masi
Keyword(s):  
Gas Turbine ◽  
Dual Fuel ◽  
Outlet Section ◽  
Outlet Temperature ◽  
Computational Domain ◽  
Gas Turbine Combustor ◽  
Fuel Gas ◽  
Turbine Inlet ◽  
Primary Zone ◽  
Better Than

The mixing process within the dilution zone noticeably affects the temperature field in the outlet section of a gas turbine combustor. In fact, dilution jets lower the temperature of the hot flow exiting the primary zone establishing suitable temperature profile and pattern factor at the combustor outlet. Thus, the dilution zone design has a significant impact on performance and durability of the turbine. In this study, a dual-fuel gas turbine combustor is investigated by a commercial finite-volume CFD code. The computational domain extends from the compressor discharge to the gas turbine inlet and it is meshed with a coarse grid since it was originally conceived for thermoacoustic analysis. The model has been already validated throughout measurements acquired during full scale isothermal and reactive tests. On the basis of the results of reactive simulations, several solutions of the dilution zone are designed to improve the uniformity of radial and circumferential temperature at the turbine inlet. The designed configurations feature number, arrangement and diameter of dilution holes which differ from the commercial configuration providing four identical dilution holes equally spaced. Advantages and drawbacks of each dilution zone layout are supported by results of numerical calculations. The results suggest that the solutions featuring two dilution holes perform better than the actual layout.

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.

scholarly journals The Development of a Diesel Burning Combustion Chamber With a Multiple Jet Primary Zone

1987 ◽  
Author(s):  
R. V. Cottington ◽  
J. P. D. Hakluytt ◽  
J. R. Tilston
Keyword(s):  
Gas Turbine ◽  
Shear Layers ◽  
Fuel Quality ◽  
Carbon Formation ◽  
Gas Turbine Combustor ◽  
Smoke Emission ◽  
Primary Zone ◽  
Efficient Combustion ◽  
Operational Range ◽  
Lean Conditions

A new primary zone for a gas turbine combustor has been developed which achieves efficient combustion in fuel lean conditions for minimizing carbon formation. This uses a large number of jets in the head of the chamber to generate independent shear layers in a co-operative array. Good combustion performance, wide fuel/air ratio operational range and tolerance to fuel quality have been demonstrated on research rigs. The combustor itself has been developed to an engine standard for a naval gas turbine required to operate with low smoke emission on distillate diesel fuel. The rig programme used to optimise the design is described together with results from engine evaluation. Practical advantages of this type of chamber apply equally to aero applications on kerosene.

The Influence of Film Cooling on Emissions for a Low NOx Radial Swirler Gas Turbine Combustor

2001 ◽  
Author(s):  
G. E. Andrews ◽  
M. N. Kim
Keyword(s):  
Mach Number ◽  
Gas Turbine ◽  
Flow Rate ◽  
Film Cooling ◽  
Equivalence Ratio ◽  
Air Flow ◽  
Gas Turbine Combustor ◽  
Cooling Flow ◽  
Full Coverage ◽  
Primary Zone

An experimental investigation was undertaken of the influence on emissions of full coverage discrete hole film cooling of a lean low NOx radial swirler natural gas combustor. The combustor used radial swirler vane passage fuel injection on the centre of the vane passage inlet. The test configuration was similar to that used in the Alstom Power Tornado and related family of low NOx gas turbines. The test conditions were simulated at atmospheric pressure at the flow condition of lean low NOx gas turbine primary zones. The tests were carried out at an isothermal flow Mach number of 0.03, which represents 60% of industrial gas turbine combustor airflow through the swirl primary zone. The effusion film cooling used was Rolls-Royce Transply, which has efficient internal cooling of the wall as well as full coverage discrete hole film cooling. Film cooling levels of 0, 16 and 40% of the primary zone airflow were investigated for a fixed total primary zone air flow and reference Mach number of 0.03. The results showed that there was a major increase in the NOx emissions for 740K inlet temperature and 0.45 overall equivalence ratio from 6ppm at zero film cooling air flow to 32ppm at 40% coolant flow rate. CO emissions increased from 25ppm to 75ppm for the same increase in film cooling flow rate. It was shown that the main effect was the creation of a richer inner swirler combustion with a surrounding film cooling flow that did not mix well with the central swirling combustion. The increase in NOx and CO could be predicted on the basis of the central swirl flow equivalence ratio.

Numerical Simulation for the Preliminary Design of Fuel Flexible Stationary Gas Turbine Combustors Using Conventional and Alternative Fuels

2012 ◽  
Author(s):  
Washington Orlando Irrazabal Bohorquez ◽  
João Roberto Barbosa ◽  
Rob Johan Maria Bastiaans ◽  
Philip de Goey
Keyword(s):  
Numerical Simulation ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Alternative Fuels ◽  
High Efficiency ◽  
Numerical Study ◽  
Operating Conditions ◽  
Pollutant Emissions ◽  
Gas Turbine Combustor ◽  
Primary Zone

Currently, high efficiency and low emissions are most important requisites for the design of modern gas turbines due to the strong environmental restrictions around the world. In the past years, alternative fuels have been considered for application in industrial gas turbines. Therefore, combustor performance, pollutant emissions and the ability to burn several fuels became of much concern and high priority has been given to the combustor design. This paper describes a methodology focused on the design of stationary gas turbines combustion chambers with the ability to efficiently burn conventional and alternative fuels. A simplified methodology is used for the calculations of the equilibrium temperature and chemical species in the primary zone of a gas turbine combustor. Direct fuel injection and diffusion flames, together with numerical methods like Newton-Raphson, LU Factorization and Lagrange Polynomials, are used for the calculations. Diesel, ethanol and methanol fuels were chosen for the numerical study. A computer code sequentially calculates the main geometry of the combustor. From the numerical simulation it is concluded that the basic gas turbine combustor geometry, for some operating conditions and burning diesel, ethanol or methanol, are of similar sizes, because the development of aerodynamic characteristics predominate over the thermochemical properties. It is worth to note that the type of fuel has a marked effect on the stability and combustion advancement in the combustor. This can be seen when the primary zone is analyzed under a steady-state operating condition. At full power, the pressure is 1.8 MPa and the temperature 1,000 K at the combustor inlet. Then, the equivalence ratios in the primary zone are 1.3933 (diesel), 1.4352 (ethanol) and 1.3977 (methanol) and the equilibrium temperatures for the same operating conditions are 2,809 K (diesel), 2,754 K (ethanol) and 2,702 K (methanol). This means that the combustor can reach similar flame stability conditions, whereas the combustion efficiency will require richer fuel/air mixtures of ethanol or methanol are burnt instead of diesel. Another important result from the numerical study is that the concentration of the main pollutants (CO, CO2, NO, NO2) is reduced when ethanol or methanol are burnt, in place of diesel.

Design and Testing of an Ultra-Low NOx Gas Turbine Combustor

1986 ◽  
Author(s):  
Kenneth O. Smith ◽  
Leonard C. Angello ◽  
F. Richard Kurzynske
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Catalytic Reduction ◽  
Water Injection ◽  
Nox Emissions ◽  
Combustion System ◽  
Gas Turbine Combustor ◽  
Program Goal ◽  
Primary Zone ◽  
Design And Testing

The design and initial rig testing of an ultra-low NOx gas turbine combustor primary zone are described. A lean premixed, swirl-stabilized combustor was evaluated over a range of pressures up to 10.7 × 105 Pa (10.6 atm) using natural gas. The program goal of reducing NOx emissions to 10 ppm (at 15% O2) with coincident low CO emissions was achieved at all combustor pressure levels. Appropriate combustor loading for ultra-low NOx operation was determined through emissions sampling within the primary zone. The work described represents a first step in developing an advanced gas turbine combustion system that can yield ultra-low NOx levels without the need for water injection and selective catalytic reduction.

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