Full Annular Rig Development of the FT8 Gas Turbine Combustor

1992 ◽  
Vol 114 (1) ◽  
pp. 27-32 ◽  
Author(s):  
T. G. Fox ◽  
B. C. Schlein
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Water Injection ◽  
Gas Turbine Combustor ◽  
Exit Temperature ◽  
Reduce Emissions ◽  
Engine Testing ◽  
And Performance ◽  
Industrial Gas Turbine ◽  
Emissions And Performance

The results of developmental testing in a high-pressure, full annular combustion section of the FT8 industrial gas turbine are presented. Base power conditions were simulated at approximately 60 percent of burner pressure. All aspects of combustion performance with liquid fuel were investigated, including starting, blowout, exit temperature signature, emissions, smoke, and liner wall temperature. Configurational change were made to improve liner cooling, reduce emissions, adjust pressure loss, and modify exit temperature profile. The effects of water injection on emissions and performance were evaluated in the final test run. Satisfactory performance in all areas was demonstrated with further refinements to be carried out during developmental engine testing.

scholarly journals Full Annular Rig Development of the FT8 Gas Turbine Combustor

1990 ◽  
Author(s):  
T. G. Fox ◽  
B. C. Schlein
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Water Injection ◽  
Gas Turbine Combustor ◽  
Exit Temperature ◽  
Reduce Emissions ◽  
Engine Testing ◽  
And Performance ◽  
Industrial Gas Turbine ◽  
Emissions And Performance

The results of developmental testing in a high pressure, full annular combustion section af the FT8 industrial gas turbine are presented. Base power conditions were simulated at approximately 60% of burner pressure. All aspects of combustion performance with liquid fuel were investigated, including starting, blowout, exit temperature signature, emissions, smoke and liner wall temperature. Configurational changes were made to improve liner cooling, reduce emissions, adjust pressure loss and modify exit temperature profile. The effects of water injection on emissions and performance were evaluated in the final test run. Satisfactory performance in all areas was demonstrated with further refinements to be carried out during developmental engine testing.

Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor

2013 ◽  
Vol 117 (1198) ◽  
pp. 1249-1271 ◽  
Author(s):  
B. Khandelwal ◽  
A. Karakurt ◽  
V. Sethi ◽  
R. Singh ◽  
Z. Quan
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Gas Turbine Combustor ◽  
Detailed Method ◽  
Low Emission ◽  
Heat Shields ◽  
Lean Fuel ◽  
Reduce Emissions ◽  
And Performance

Abstract Modern gas turbine combustor design is a complex task which includes both experimental and empirical knowledge. Numerous parameters have to be considered for combustor designs which include combustor size, combustion efficiency, emissions and so on. Several empirical correlations and experienced approaches have been developed and summarised in literature for designing conventional combustors. A large number of advanced technologies have been successfully employed to reduce emissions significantly in the last few decades. There is no literature in the public domain for providing detailed design methodologies of triple annular combustors. The objective of this study is to provide a detailed method designing a triple annular dry low emission industrial combustor and evaluate its performance, based on the operating conditions of an industrial engine. The design methodology employs semi-empirical and empirical models for designing different components of gas turbine combustors. Meanwhile, advanced DLE methods such as lean fuel combustion, premixed methods, staged combustion, triple annular, multi-passage diffusers, machined cooling rings, DACRS and heat shields are employed to cut down emissions. The design process is shown step by step for design and performance evaluation of the combustor. The performance of this combustor is predicted, it shows that NO x emissions could be reduced by 60%-90% as compared with conventional single annular combustors.

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 Emissions and Performance of Catalysts for Gas Turbine Catalytic Combustors

1977 ◽  
Author(s):  
D. N. Anderson
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Temperature Pattern ◽  
Turbine Engine ◽  
Reference Velocity ◽  
Test Conditions ◽  
Exit Temperature ◽  
And Performance ◽  
Catalytic Combustor ◽  
Emissions And Performance

Three noble-metal monolithic catalysts were tested in a 12-cm-dia combustion test rig to obtain emissions and performance data at conditions simulating the operation of a catalytic combustor for an automotive gas turbine engine. Tests with one of the catalysts at 800 K inlet mixture temperature, 3 × 105 Pa (3 atm) pressure, and a reference velocity (catalyst bed inlet velocity) of 10 m/sec demonstrated greater than 99 percent combustion efficiency for reaction temperatures higher than 1300 K. With a reference velocity of 25 m/sec the reaction temperature required to achieve the same combustion efficiency increased to 1380 K. The exit temperature pattern factors for all three catalysts were below 0.1 when adiabatic reaction temperatures were higher than 1400 K. The highest pressure drop was 4.5 percent at 25 m/sec reference velocity. Nitrogen oxides emissions were less than 0.1 g NO2/kg fuel for all test conditions.

Performance Prediction of Gas Turbine Under Different Strategies Using Low Heating Value Fuel

2013 ◽  
Author(s):  
Edson Batista da Silva ◽  
Marcelo Assato ◽  
Rosiane Cristina de Lima
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Equivalence Ratio ◽  
Safe Operation ◽  
Engine Operation ◽  
Heating Value ◽  
Gasification Process ◽  
Surge Margin ◽  
And Performance ◽  
Industrial Gas Turbine

Usually, the turbogenerators are designed to fire a specific fuel, depending on the project of these engines may be allowed the operation with other kinds of fuel compositions. However, it is necessary a careful evaluation of the operational behavior and performance of them due to conversion, for example, from natural gas to different low heating value fuels. Thus, this work describes strategies used to simulate the performance of a single shaft industrial gas turbine designed to operate with natural gas when firing low heating value fuel, such as biomass fuel from gasification process or blast furnace gas (BFG). Air bled from the compressor and variable compressor geometry have been used as key strategies by this paper. Off-design performance simulations at a variety of ambient temperature conditions are described. It was observed the necessity for recovering the surge margin; both techniques showed good solutions to achieve the same level of safe operation in relation to the original engine. Finally, a flammability limit analysis in terms of the equivalence ratio was done. This analysis has the objective of verifying if the combustor will operate using the low heating value fuel. For the most engine operation cases investigated, the values were inside from minimum and maximum equivalence ratio range.

Predicting Thermoacoustic Instability in an Industrial Gas Turbine Combustor: Combining a Low Order Network Model With Flame LES

2017 ◽  
Author(s):  
Y. Xia ◽  
A. S. Morgans ◽  
W. P. Jones ◽  
J. Rogerson ◽  
G. Bulat ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Acoustic Waves ◽  
Gas Turbine Combustor ◽  
Network Modelling ◽  
Weakly Nonlinear ◽  
Thermoacoustic Instability ◽  
Reduced Chemistry ◽  
Flame Describing Function ◽  
Industrial Gas Turbine ◽  
Low Order

The thermoacoustic modes of a full scale industrial gas turbine combustor have been predicted numerically. The predictive approach combines low order network modelling of the acoustic waves in a simplified geometry, with a weakly nonlinear flame describing function, obtained from incompressible large eddy simulations of the flame region under upstream forced velocity perturbations, incorporating reduced chemistry mechanisms. Two incompressible solvers, each employing different numbers of reduced chemistry mechanism steps, are used to simulate the turbulent reacting flowfield to predict the flame describing functions. The predictions differ slightly between reduced chemistry approximations, indicating the need for more involved chemistry. These are then incorporated into a low order thermoacoustic solver to predict thermoacoustic modes. For the combustor operating at two different pressures, most thermoacoustic modes are predicted to be stable, in agreement with the experiments. The predicted modal frequencies are in good agreement with the measurements, although some mismatches in the predicted modal growth rates and hence modal stabilities are observed. Overall, these findings lend confidence in this coupled approach for real industrial gas turbine combustors.

scholarly journals Swirl-Can Combustor Performance to Near-Stoichiometric Fuel-Air Ratio

1976 ◽  
Author(s):  
L. A. Diehl ◽  
J. A. Biaglow
Keyword(s):  
Air Temperature ◽  
Combustion Efficiency ◽  
Oxides Of Nitrogen ◽  
Module Design ◽  
Air Temperatures ◽  
Nitrogen Emission ◽  
Unburned Hydrocarbons ◽  
Exit Temperature ◽  
And Performance ◽  
Emissions And Performance

Emissions and performance characteristics were determined for two full-annulus swirl-can modular combustors operated to near-stoichiometric fuel air ratios. The purposes of the tests were to obtain stoichiometric data at inlet-air temperatures up to 894 K and to determine the effect of module number by investigating 120 and 72 module swirl-can combustors. The maximum average exit temperature obtained with the 120-module swirl-can combustor was 2465 K with a combustion efficiency of 95 percent at an inlet-air temperature of 894 K. The 72-module swirl-can combustor reached a maximum average exit temperature of 2306 K with a combustion efficiency of 92 percent at an inlet-air temperature of 894 K. At a constant inlet air temperature, maximum oxides of nitrogen emission index values occurred at a fuel-air ratio of 0.037 for the 72-module design and 0.044 for the 120-module design. The combustor average exit temperature and combustion efficiency were calculated from emissions measurements. The measured emissions included carbon monoxide, unburned hydrocarbons, oxides of nitrogen, and smoke.

Experimental Assessment of the Emissions Benefits of a Ceramic Gas Turbine Combustor

1996 ◽  
Author(s):  
K. O. Smith ◽  
A. Fahme
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Flow Distribution ◽  
Operating Conditions ◽  
Nox Emissions ◽  
Fuel Injector ◽  
Gas Turbine Combustor ◽  
Experimental Assessment ◽  
Industrial Gas Turbine ◽  
Combustor Liner

Three subscale, cylindrical combustors were rig tested on natural gas at typical industrial gas turbine operating conditions. The intent of the testing was to determine the effect of combustor liner cooling on NOx and CO emissions. In order of decreasing liner cooling, a metal louvre-cooled combustor, a metal effusion-cooled combustor, and a backside-cooled ceramic (CFCC) combustor were evaluated. The three combustors were tested using the same lean-premixed fuel injector. Testing showed that reduced liner cooling produced lower CO emissions as reaction quenching near the liner wall was reduced. A reduction in CO emissions allows a reoptimization of the combustor air flow distribution to yield lower NOx emissions.

Investigation on flame characteristics of industrial gas turbine combustor with different mixing uniformities

Fuel ◽  
2020 ◽  
Vol 259 ◽  
pp. 116297 ◽  
Author(s):  
Zhihao Zhang ◽  
Xiao Liu ◽  
Yaozhen Gong ◽  
Zhiming Li ◽  
Jialong Yang ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Combustor ◽  
Industrial Gas Turbine
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