Development of a Lean-Premixed Two-Stage Annular Combustor for Gas Turbine Engines

1994 ◽  
Author(s):  
Fred C. Bahlmann ◽  
B. Martien Visser
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Emission Characteristics ◽  
Gas Turbine Engines ◽  
Two Stage ◽  
Low Emission ◽  
Lean Premixed ◽  
Annular Combustor

The development, from concept to hardware of a lean-premixed two-stage combustor for small gas turbine engines is presented. This Annular Low Emission Combustor (ALEC) is based on a patent of R.J. Mowill. Emission characteristics of several prototypes of this combustor under a variety of conditions are presented. It is shown that ultra-low NOx levels (< 10 ppm) can be reached with satisfactory CO levels (< 50 ppm).

Fuel Flexibility in LM2500 and LM6000 Dry Low Emission Engines

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
John Blouch ◽  
Hejie Li ◽  
Mark Mueller ◽  
Richard Hook
Keyword(s):  
Gas Turbine ◽  
Operating Conditions ◽  
Inert Gases ◽  
Effect Of Temperature ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Kinetics Analysis ◽  
Fuel Flexibility ◽  
Low Emission ◽  
Commercial Operation

The LM2500 and LM6000 dry-low-emissions aeroderivative gas turbine engines have been in commercial service for 15 years and have accumulated nearly 10 × 106 hours of commercial operation. The majority of these engines utilize pipeline quality natural gas predominantly comprised of methane. There is; however, increasing interest in nonstandard fuels that contain varying levels of higher hydrocarbon species and/or inert gases. This paper reports on the demonstrated operability of LM2500 and LM6000 DLE engines with nonstandard fuels. In particular, rig tests at engine conditions were performed to demonstrate the robustness of the dual-annular counter-rotating swirlers premixer design, relative to flameholding with fuels containing high ethane, propane, and N2 concentrations. These experiments, which test the ability of the hardware to shed a flame introduced into the premixing region, have been used to expand the quoting limits for LM2500 and LM6000 gas turbine engines to elevated C2+ levels. In addition, chemical kinetics analysis was performed to understand the effect of temperature, pressure, and fuel compositions on flameholding. Test data for different fuels and operating conditions were successfully correlated with Damkohler number.

Fuel Flexibility in LM2500 and LM6000 Dry Low Emission Engines

2011 ◽  
Author(s):  
John Blouch ◽  
Hejie Li ◽  
Mark Mueller ◽  
Richard Hook
Keyword(s):  
Gas Turbine ◽  
Operating Conditions ◽  
Inert Gases ◽  
Effect Of Temperature ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Kinetics Analysis ◽  
Fuel Flexibility ◽  
Low Emission ◽  
Commercial Operation

The LM2500 and LM6000 dry-low-emissions (DLE) aeroderivative gas turbine engines have been in commercial service for 15 years and have accumulated nearly 10 million hours of commercial operation. The majority of these engines utilize pipeline quality natural gas predominantly comprised of methane. There is, however, increasing interest in nonstandard fuels that contain varying levels of higher hydrocarbon species and/or inert gases. This paper reports on the demonstrated operability of LM2500 and LM6000 DLE engines with nonstandard fuels. In particular, rig tests at engine conditions were performed to demonstrate the robustness of the dual-annular counter-rotating swirlers (DACRS) premixer design, relative to flameholding with fuels containing high ethane, propane, and N2 concentrations. These experiments, which test the ability of the hardware to shed a flame introduced into the premixing region, have been used to expand the quoting limits for LM2500 and LM6000 gas turbine engines to elevated C2+ levels. In addition, chemical kinetics analysis was performed to understand the effect of temperature, pressure, and fuel compositions on flameholding. Test data for different fuels and operating conditions were successfully correlated with Damkohler number.

Analysis of emission characteristics of gas turbine engines with some alternative fuels

2017 ◽  
Vol 15 (3) ◽  
pp. 161-168 ◽  
Author(s):  
A. M. Starik ◽  
A. M. Savel’ev ◽  
O. N. Favorskii ◽  
N. S. Titova
Keyword(s):  
Gas Turbine ◽  
Alternative Fuels ◽  
Turbine Engines ◽  
Emission Characteristics ◽  
Gas Turbine Engines

The Reduction of Gas Turbine Idle Emissions by Fuel Zoning for Compressor Bleed

1974 ◽  
Vol 96 (3) ◽  
pp. 807-810
Author(s):  
T. R. Clements
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbofan Engine ◽  
Total Hydrocarbon ◽  
Annular Combustor ◽  
Full Power

Two methods of reducing the idle emissions of gas turbine engines have been investigated. The methods were (1) fuel zoning, whereby a portion of the fuel nozzles were shut down and all of the fuel passed through the remaining nozzles and (2) larger than normal compressor overboard bleed. Both methods operate on the fact that a combustor’s efficiency increases as the fuel/air ratio is increased from idle to full power conditions. Fuel zoning increases the local fuel/air ratio making those portions of the combustor which are operating more efficient. This method has been shown to reduce the idle emission of total hydrocarbon by 5 to 1 in a double annular combustor sized for a large augmented turbofan engine. Operating with a larger than normal compressor overboard bleed allows increasing fuel/air ratio without increasing idle thrust. By using this method in a P&WA™ JT3C-7 engine a reduction of 2 to 1 in the emission of total hydrocarbon was demonstrated.

Exhaust Emission Characteristics of Aircraft Gas Turbine Engines

1972 ◽  
Author(s):  
A. W. Nelson
Keyword(s):  
Gas Turbine ◽  
Environmental Protection Agency ◽  
Turbine Engines ◽  
Exhaust Emission ◽  
Emission Characteristics ◽  
Gas Turbine Engines ◽  
Protection Agency ◽  
Variation Characteristics ◽  
Exhaust Stream ◽  
Documentation Program

Accurate measurement of the exhaust emissions of aircraft gas turbine engines presents a challenge not only because of the high velocities and temperatures of the exhaust stream, but also because of the variation of the exhaust constitutents over the relatively large-cross-section of the jet stream itself. Other factors which affect exhaust emission level include ambient temperature and humidity. This paper presents the results of independent efforts by Pratt & Whitney Aircraft to identify emission variation characteristics together with results of an exhaust emission documentation program funded by the Environmental Protection Agency. Methods and techniques employed in the above programs are also discussed. The results of these programs indicate that additional effort is required to properly evaluate and understand the emission characteristics of aircraft gas turbine engines.

Lowest emission sustainable aviation biofuels as the potential replacement for the Jet-A fuels

2020 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Anderson A. ◽  
Karthikeyan A. ◽  
Ramesh Kumar C. ◽  
Ramachandran S. ◽  
Praveenkumar T.R.
Keyword(s):  
Gas Turbine ◽  
Fossil Fuels ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Emission Characteristics ◽  
Gas Turbine Engines ◽  
Content Type ◽  
Turbine Engine ◽  
Micro Gas Turbine ◽  
Fuel Blends

Purpose The purpose of this study is to predict the performance and emission characteristics of micro gas turbine engines powered by alternate fuels. The micro gas turbine engine performance, combustion and emission characteristics are analyzed for the jet fuel with different additives. Design/methodology/approach The experimental investigation was carried out with Jet A-1 fuel on the gas turbine engines at different load conditions. The primary blends of the Jet A-1 fuels are from canola and solid waste pyrolysis oil. Then the ultrasonication of highly concentrated multiwall carbon nanotubes is carried with the primary blends of canola (Jet-A fuel 70%, canola 20% and 10% ethanol) and P20E (Jet-A 70% fuel, 20% PO and 10% ethanol). Findings The consumption of the fuel is appreciable with the blends at a very high static thrust. The 39% reduction in thrust specific fuel consumption associated with a 32% enhance in static thrust with P20E blend among different fuel blends. Moreover, due to the increase in ethanol concentration in the blends PO20E and C20E lead to a 22% rise in thermal efficiency and a 9% increase in higher oxygen content is observed. Practical implications The gas turbine engine emits very low emission of gases such as CO, CO2 and NOx by using the fuel blends, which typically reduces the fossil fuel usage limits with reduced pollutants. Originality/value The emission of the gas turbine engines is further optimized with the addition of hydrogen in Jet-A fuel. That is leading to high specific fuel exergy and owing to the lower carbon content in the hydrogen fuel when compared with that of the fossil fuels used in gas turbine engines. Therefore, the usage of hydrogen with nanofluids was so promising based on the results obtained for replacing fossil fuels.

Numerical Investigation of Ignition Sequence in a Multi-Burner Methane-Air Swirl Combustor Using Flamelet Generated Manifold Combustion Model

2019 ◽  
Author(s):  
Pravin Nakod ◽  
Sourabh Shrivastava ◽  
Saurabh Patwardhan ◽  
Stefano Orsino ◽  
Rakesh Yadav
Keyword(s):  
Experimental Data ◽  
Numerical Investigation ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Combustion Model ◽  
Gas Turbine Engines ◽  
Swirl Combustor ◽  
Low Emission ◽  
Flamelet Generated Manifold ◽  
Work Assessment

Abstract Low emission gas turbine engines, operating under fuel lean conditions, are susceptible to light-around issues. Traditionally, gas turbine manufacturers rely on experimentation and testing to understand the relight characteristics of a combustor. However, since the last decade, numerical simulations are gaining popularity in performance evaluation of the light-around characteristics of the gas turbine combustors. In the present work, assessment of the Flamelet Generated Manifold (FGM) combustion model is carried out to understand its performance for capturing the correct ignition sequence in a linear multi-burner methane-air swirl combustor designed by COmplexe de Recherche Interprof essionnel en Aérothermochimie (CORIA) in the context of Knowledge for Ignition, Acoustics, and Instabilities (KIAI) project. The present work uses linear five, four and two swirled injector configurations for the validation of the simulation results. Non-reacting and reacting Large Eddy Simulations (LES) are performed for three injector arrangements to predict the main flow structure, mixing, flame propagation and ignition sequence. Non-reacting time-averaged flow quantities such as mean axial and radial velocities are data-sampled and compared with the experimental results. The predicted results show a good comparison between simulation and experimental data. Ignition sequence and timing predicted from the reacting LES for all the three configurations studied in this work, also compare well with the experimental data. This numerical investigation confirms that the FGM combustion model used in the LES framework can be successfully employed for the prediction of the relight characteristics of the gas turbine engines.

Empirical and Semi-Empirical Correlation of Emissions Data From Modern Turbopropulsion Gas Turbine Engines

1996 ◽  
Author(s):  
Allen M. Danis ◽  
Byron A. Pritchard ◽  
Hukam C. Mongia
Keyword(s):  
Gas Turbine ◽  
Empirical Correlation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Reactor Modeling ◽  
Annular Combustor ◽  
Unburned Hydrocarbons ◽  
Semi Empirical ◽  
Operating Points ◽  
Unique Relationship

The engine certification emissions data from a CFM56 single-annular combustor (SAC), the CFM56 dual-annular combustor (DAC), the CF6-80C SAC and the CF6-80C SAC low-emissions configuration (LEC) were used to show the following: (1) NOxEI can be correlated as a function of P3 and T3. (2) There is a unique relationship between NOx, CO and unburned hydrocarbons (HC). (3) NOx, CO and HC for engine operating points can be predicted reasonably well through “single reactor” modeling. However, the resulting NOx/CO/HC relationship is not as well predicted indicating need for further improving the semiempirical methodology.

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