Technology Update on Gas Turbine Dual Fuel, Dry Low Emission Combustion Systems

2003 ◽  
Author(s):  
Petter Egil Ro̸kke ◽  
Johan E. Hustad ◽  
Nils A. Ro̸kke ◽  
Ole Birger Svendsgaard
Keyword(s):  
Gas Turbine ◽  
Flame Temperature ◽  
Steam Injection ◽  
Dual Fuel ◽  
Combustion System ◽  
Single Digit ◽  
Water Steam ◽  
Marine Propulsion ◽  
Low Emission ◽  
Combustion Systems

A challenging issue in the gas turbine industry is to develop a practical dual fuel (DF), dry low emission (DLE) combustion system. Especially for the onshore-based power generation systems, and liquid DLE for aeroderivative engines used for marine propulsion. A novel mid-size (3MW) gas turbine is being developed mainly targeted for marine propulsion, where a dual fuel DLE combustion system aiming at single digit NOx emission figures has been explored. As a part of this development, the present technology available from different gas turbine manufacturers has been surveyed. Status of the different techniques applied in dual fuel DLE combustors today and their achievements are presented, including the available information on fuel injectors, cooling schemes, combustion air distribution, noise control and combustor performance. The techniques utilized and explained are such as flame temperature control (water/steam injection), staged combustion, lean premixing and lean prevaporized premixing, rich-quench-lean-burning (RQLB) and catalytic combustion. These are also documented for the different concepts commercially available, describing both advantages and drawbacks. Conclusions are made towards the dominating trends for the different parameters mentioned above, and how they affect the final combustor design. A survey of the dominating parameters for low emission combustion systems is presented.

Dual Fuel Dry Low Emissions (DLE) Combustion System for the ABB Alstom Power 13,4 MW Cyclone Gas Turbine

2000 ◽  
Author(s):  
H. Alkabie ◽  
R. McMillan ◽  
R. Noden ◽  
C. Morris
Keyword(s):  
Gas Turbine ◽  
Dynamic Pressure ◽  
Pressure Ratio ◽  
Pressure Fluctuations ◽  
Steam Injection ◽  
Liquid Fuels ◽  
Dual Fuel ◽  
Outlet Temperature ◽  
Combustion System ◽  
Successful Operation

In response to stringent environmental legislation and customer demands for improved thermal efficiency, ABB ALSTOM POWER UK Ltd has introduced the 13.4MW Cyclone gas turbine engine. In this machine higher efficiency is achieved by increased firing temperature and pressure ratio. In order to meet the environmental considerations the Cyclone is supplied with Dual Fuel DLE combustion system as standard. Successful operation of the combustion system required a careful balance between the component life and low emissions performance. The combustor performance specification included targets for the following parameters:- • Low emissions, NOx, CO, UHC and smoke, on both gaseous and liquid fuels without water or steam injection • Good turn down ratio • Controlled combustor outlet temperature profiles, both OTDF and RTDF • Low dynamic pressure fluctuations • Reliable ignition and fuel change over on both gas and liquid. • Reliable transient response This paper describes the design and validation work undertaken in order to achieve these challenging targets. It is shown that these targets are not only achieved but in some cases exceeded resulting in an economical and environmentally sound combustion system.

Low-Emissions Technology Development for Auxiliary Power Unit Combustion Systems

2021 ◽  
Author(s):  
Thomas Bronson ◽  
Rudy Dudebout ◽  
Nagaraja Rudrapatna
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Fuel Injection ◽  
Oxides Of Nitrogen ◽  
Combustion System ◽  
Auxiliary Power Unit ◽  
Criteria Pollutants ◽  
Auxiliary Power ◽  
Combustion Systems ◽  
Aircraft Application

Abstract The aircraft Auxiliary Power Unit (APU) is required to provide power to start the main engines, conditioned air and power when there are no facilities available and, most importantly, emergency power during flight operation. Given the primary purpose of providing backup power, APUs have historically been designed to be extremely reliable while minimizing weight and fabrication cost. Since APUs are operated at airports especially during taxi operations, the emissions from the APUs contribute to local air quality. There is clearly significant regulatory and public interest in reducing emissions from all sources at airports, including from APUs. As such, there is a need to develop technologies that reduce criteria pollutants, namely oxides of nitrogen (NOx), unburned hydrocarbons (UHC), carbon monoxide (CO) and smoke (SN) from aircraft APUs. Honeywell has developed a Low-Emissions (Low-E) combustion system technology for the 131-9 and HGT750 family of APUs to provide significant reduction in pollutants for narrow-body aircraft application. This article focuses on the combustor technology and processes that have been successfully utilized in this endeavor, with an emphasis on abating NOx. This paper describes the 131-9/HGT750 APU, the requirements and challenges for small gas turbine engines, and the selected strategy of Rich-Quench-Lean (RQL) combustion. Analytical and experimental results are presented for the current generation of APU combustion systems as well as the Low-E system. The implementation of RQL aerodynamics is well understood within the aero-gas turbine engine industry, but the application of RQL technology in a configuration with tangential liquid fuel injection which is also required to meet altitude ignition at 41,000 ft is the novelty of this development. The Low-E combustion system has demonstrated more than 25% reduction in NOx (dependent on the cycle of operation) vs. the conventional 131-9 combustion system while meeting significant margins in other criteria pollutants. In addition, the Low-E combustion system achieved these successes as a “drop-in” configuration within the existing envelope, and without significantly impacting combustor/turbine durability, combustor pressure drop, or lean stability.

Development of a Low-Emission Combustor for a 100-kW Automotive Ceramic Gas Turbine (III)

1996 ◽  
Author(s):  
Masafumi Sasaki ◽  
Hirotaka Kumakura ◽  
Daishi Suzuki ◽  
Hiroyuki Ichikawa ◽  
Youichiro Ohkubo ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Gas Turbine ◽  
Air Distribution ◽  
Performance Tests ◽  
Test Results ◽  
Combustion System ◽  
Stable Combustion ◽  
Lean Combustion ◽  
Low Emission ◽  
Combustion Region

A low emission combustor, which uses a prevaporization-premixing lean combustion system for the 100 kW automotive ceramic gas turbine (CGT), has been subjected to performance tests. Now a second combustor prototype (PPL-2), which incorporates improvements intended to overcome a flashback problem observed in an initial combustor prototype (PPL-1), is tested. The PPL-2 has been designed and built, so that it will substantially expand the stable combustion range. The improvement is accomplished by increasing the air distribution ratio in the lean combustion region to avoid flashback, providing a uniform flow velocity through the throat area and also by diluting the boundary layer so as to suppress flashback. Test results of the PPL-2 combustor show that it expands the flashback limit without affecting the blow out limit and is able to cover the stable combustion range need for the 100kW CGT.

Development of a Low Emission Combustor for a 100kW Automotive Ceramic Gas Turbine: I

1993 ◽  
Author(s):  
Masafumi Sasaki ◽  
Hirotaka Kumakura ◽  
Daishi Suzuki ◽  
Katsuhiko Sugiyama ◽  
Youichirou Ohkubo
Keyword(s):  
Gas Turbine ◽  
Inlet Temperature ◽  
Performance Tests ◽  
Combustion System ◽  
Passenger Cars ◽  
Temperature Level ◽  
Fuel Injectors ◽  
Low Emission ◽  
Ceramic Components ◽  
Suitable System

A low emission combustor for a 100kW ceramic gas turbine, which is intended to meet Japanese emission standards for gasoline passenger cars, has been designed and subjected to initial performance tests. A prevaporization-premixing combustion system was chosen as the most suitable system for the combustor. The detailed combustor design, including the use of ceramic components and fuel injectors, was pursued taking into account the allowable engine dimensions for vehicle installation. In the initial performance tests conducted at a combustor inlet temperature of 773K, a low NOx level was obtained that satisfied the steady state target at this temperature level.

Combustion System Performance and Field Test Results of the MS7001F Gas Turbine

1993 ◽  
Vol 115 (3) ◽  
pp. 537-546 ◽  
Author(s):  
J. P. Claeys ◽  
K. M. Elward ◽  
W. J. Mick ◽  
R. A. Symonds
Keyword(s):  
Gas Turbine ◽  
Field Test ◽  
System Performance ◽  
Mechanical Performance ◽  
Steam Injection ◽  
Test Results ◽  
Combustion System ◽  
Dynamic Activity ◽  
Unburned Hydrocarbons ◽  
Nox Control

This paper presents the results of the combustion system test of the MS7001F installed at the Virginia Power Chesterfield station. Tests of water and steam injection for NOx control were performed. Results of emissions, combustor dynamics, and combustor hardware performance are presented. Emissions test results include NOx, CO, unburned hydrocarbons, VOC, and formaldehyde levels. Combustor dynamic activity over a range of diluent injection ratios, and the performance of an actively cooled transition duct are also discussed. Combustion system mechanical performance is described following the first combustion system inspection.

Full Scale Testing of a Low Swirl Fuel Injector Concept for Ultra-Low NOx Gas Turbine Combustion Systems

2006 ◽  
Author(s):  
Waseem Nazeer ◽  
Kenneth Smith ◽  
Patrick Sheppard ◽  
Robert Cheng ◽  
David Littlejohn
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Flame Temperature ◽  
Pressure Oscillation ◽  
Test Results ◽  
Combustion System ◽  
Fuel Injector ◽  
Annular Combustor ◽  
Swirl Injector ◽  
Gas Turbine Combustion

The continued development of a low swirl injector for ultra-low NOx gas turbine applications is described. An injector prototype for natural gas operation has been designed, fabricated and tested. The target application is an annular gas turbine combustion system requiring twelve injectors. High pressure rig test results for a single injector prototype are presented. On natural gas, ultra-low NOx emissions were achieved along with low CO. A turndown of approximately 100°F in flame temperature was possible before CO emissions increased significantly. Subsequently, a set of injectors was evaluated at atmospheric pressure using a production annular combustor. Rig testing again demonstrated the ultra-low NOx capability of the injectors on natural gas. An engine test of the injectors will be required to establish the transient performance of the combustion system and to assess any combustor pressure oscillation issues.

scholarly journals Investigations of the Working Process in a Dual-Fuel Low-Emission Combustion Chamber for an FPSO Gas Turbine Engine

2020 ◽  
Vol 27 (3) ◽  
pp. 89-99
Author(s):  
Serhiy Serbin ◽  
Badri Diasamidze ◽  
Marek Dzida
Keyword(s):  
Nitrogen Oxides ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Liquid Fuel ◽  
Turbulent Flame ◽  
Dual Fuel ◽  
Working Process ◽  
Fuel Supply ◽  
Low Emission ◽  
Gas Turbine Combustion

AbstractThis investigation is devoted to an analysis of the working process in a dual-fuel low-emission combustion chamber for a floating vessel’s gas turbine. The low-emission gas turbine combustion chamber with partial pre-mixing of fuel and air inside the outer and inner radial-axial swirlers was chosen as the object of research. When modelling processes in a dual-flow low-emission gas turbine combustion chamber, a generalized method is used, based on the numerical solution of the system of conservation and transport equations for a multi-component chemically reactive turbulent system, taking into consideration nitrogen oxides formation. The Eddy-Dissipation-Concept model, which incorporates Arrhenius chemical kinetics in a turbulent flame, and the Discrete Phase Model describing the interfacial interaction are used in the investigation. The obtained results confirmed the possibility of organizing efficient combustion of distillate liquid fuel in a low-emission gas turbine combustion chamber operating on the principle of partial preliminary formation of a fuel-air mixture. Comparison of four methods of liquid fuel supply to the channels of radial-axial swirlers (centrifugal, axial, combined, and radial) revealed the advantages of the radial supply method, which are manifested in a decrease in the overall temperature field non-uniformity at the outlet and a decrease in nitrogen oxides emissions. The calculated concentrations of nitrogen oxides and carbon monoxide at the flame tube outlet for the radial method of fuel supply are 32 and 9.1 ppm, respectively. The results can be useful for further modification and improvement of the characteristics of dual-fuel gas turbine combustion chambers operating with both gaseous and liquid fuels.

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