scholarly journals An Advanced Development of a Second-Generation Dry, Low-NOx Combustor for 1.5MW Gas Turbine

1996 ◽  
Author(s):  
Shin-ichi Kajita ◽  
Shin-ichi Ohga ◽  
Masahiro Ogata ◽  
Satoru Itaka ◽  
Jun-ichi Kitajima ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Second Generation ◽  
Nox Reduction ◽  
Combustion Efficiency ◽  
Combustion System ◽  
Endurance Test ◽  
Industrial Gas Turbine ◽  
Cooling Air ◽  
Cycle Endurance ◽  
Advanced Development

Advanced development of a second-generation dry, low-NOx combustor for KHI’s 1.5MW industrial gas turbine, M1A-13A, is described. In this advanced development, efforts were made mainly to improve combustion efficiency in addition to NOx reduction experimentally. The combustion liner was extended to increase combustion volume, and supplemental burners were installed downstream of multiple main burners to broaden low-NOx operation range. In consequence of the optimization of the fuel allotment, air/fuel ratio at each burner, cooling air, and so on, the engine showed NOx emissions under 15 ppm (15% O2), and a combustion efficiency more than 99.5% over the range between 75% and 100% load. Finally, by means of a 300-hour operation at full load and a 500-cycle endurance test, the total reliability of this combustion system was ensured.

scholarly journals The Design Modifications of the EGT Tornado Industrial Gas Turbine to Incorporate a Dry Low Emissions Combustion System

1997 ◽  
Author(s):  
Stephen Gallimore ◽  
R. Michael Vickers ◽  
Michael B. Boyns
Keyword(s):  
Gas Turbine ◽  
Nox Reduction ◽  
Steam Injection ◽  
Emissions Reduction ◽  
Combustion System ◽  
Gas Generator ◽  
And Performance ◽  
Compact Design ◽  
Performance Validation ◽  
Industrial Gas Turbine

The Tornado gas turbine was designed at a time when emissions legislation was minimal and was developed through the eighties to accept water or steam injection for NOX reduction. In recent years it has become necessary to develop dry methods of emissions reduction for new engine sales and to enable existing operators to retrofit their engines when legislation demands. The compact design of the Tornado’s centre section did not lend itself to a simple combustor changeout. The lean pre-mix dry low emissions (DLE) system developed for the Typhoon gas turbine required additional combustor length for CO burnout and could not be fitted into the existing casings of the Tornado engine. The challenge was therefore to redesign the centre section to enable the DLE system to be fitted without compromising the design of the compressor, HP turbine and gas generator rotor. This paper describes the methodology used and the design of the engine centre section together with the results of design and performance validation undertaken including emissions measurements.

Siemens SGT-800 Industrial Gas Turbine Enhanced to 50MW: Combustor Design Modifications, Validation and Operation Experience

2013 ◽  
Author(s):  
Daniel Lörstad ◽  
Annika Lindholm ◽  
Jan Pettersson ◽  
Mats Björkman ◽  
Ingvar Hultmark
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Cooling System ◽  
Good Condition ◽  
Combined Cycle ◽  
Combustion Stability ◽  
Combustion System ◽  
Design Work ◽  
Engine Operation ◽  
Cooling Air

Siemens Oil & Gas introduced an enhanced SGT-800 gas turbine during 2010. The new power rating is 50.5MW at a 38.3% electrical efficiency in simple cycle (ISO) and best in class combined-cycle performance of more than 55%, for improved fuel flexibility at low emissions. The updated components in the gas turbine are interchangeable from the existing 47MW rating. The increased power and improved efficiency are mainly obtained by improved compressor airfoil profiles and improved turbine aerodynamics and cooling air layout. The current paper is focused on the design modifications of the combustor parts and the combustion validation and operation experience. The serial cooling system of the annular combustion chamber is improved using aerodynamically shaped liner cooling air inlet and reduced liner rib height to minimize the pressure drop and optimize the cooling layout to improve the life due to engine operation hours. The cold parts of the combustion chamber were redesigned using cast cooling struts where the variable thickness was optimized to maximize the cycle life. Due to fewer thicker vanes of the turbine stage #1, the combustor-turbine interface is accordingly updated to maintain the life requirements due to the upstream effect of the stronger pressure gradient. Minor burner tuning is used which in combination with the previously introduced combustor passive damping results in low emissions for >50% load, which is insensitive to ambient conditions. The combustion system has shown excellent combustion stability properties, such as to rapid load changes and large flame temperature range at high loads, which leads to the possibility of single digit Dry Low Emission (DLE) NOx. The combustion system has also shown insensitivity to fuels of large content of hydrogen, different hydrocarbons, inerts and CO. Also DLE liquid operation shows low emissions for 50–100% load. The first SGT-800 with 50.5MW rating was successfully tested during the Spring 2010 and the expected performance figures were confirmed. The fleet leader has, up to January 2013, accumulated >16000 Equivalent Operation Hours (EOH) and a planned follow up inspection made after 10000 EOH by boroscope of the hot section showed that the combustor was in good condition. This paper presents some details of the design work carried out during the development of the combustor design enhancement and the combustion operation experience from the first units.

scholarly journals Testing of a Full Scale, Low Emissions, Ceramic Gas Turbine Combustor

1997 ◽  
Author(s):  
K. Smith ◽  
A. Fahme
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Combustion Efficiency ◽  
Full Scale ◽  
Significant Deterioration ◽  
Lean Premixed Combustion ◽  
Fuel Injectors ◽  
Primary Zone ◽  
Test Engine ◽  
Cooling Air

The design and development testing of a full scale, low emissions, ceramic combustor for a 5500 HP industrial gas turbine are described. The combustor was developed under a joint program conducted by the U.S. DOE and Solar Turbines. The ceramic combustor is designed to replace the production Centaur 50S SoLoNOx burner which uses lean-premixed combustion to limit NOx and CO to 25 and 50 ppm, respectively. Both the ceramic and production combustors are annular in shape and employ twelve premixing, natural gas fuel injectors. The ceramic combustor design effort involved the integration of two CFCC cylinders (76.2 cm [30 in.] and 35.56 cm [14 in.] diameters) into the combustor primary zone. The ceramic combustor was evaluated at Solar in full scale test rigs and a test engine. Performance of the combustor was excellent with high combustion efficiency and extremely low NOx and CO emissions. The hot walls of the ceramic combustor played a significant role in reducing CO emissions. This suggests that liner cooling air injected through the metal production liner contributes to CO emissions by reaction quenching at the liner walls. It appears that ceramics can serve to improve combustion efficiency near the combustor lean limit which, in turn, would allow further reductions in NOx emissions. Approximately 50 hours of operation have been accumulated using the ceramic combustor. No significant deterioration in the CFCC liners has been observed. A 4000 hour field test of the combustion system is planned to begin in 1997 as a durability assessment.

scholarly journals Mars™ SoLoNOx Combustion System CFD Modeling

1995 ◽  
Author(s):  
Matthew E. Thomas ◽  
Mark J. Ostrander ◽  
Andy D. Leonard ◽  
Mel Noble ◽  
Colin Etheridge
Keyword(s):  
Gas Turbine ◽  
System Development ◽  
Cfd Modeling ◽  
Cfd Analysis ◽  
Combustion System ◽  
Design Environment ◽  
Turbine Engine ◽  
Combustion Modeling ◽  
Premix Combustion ◽  
Industrial Gas Turbine

CFD analysis methods were successfully implemented and verified with ongoing industrial gas turbine engine lean premix combustion system development. Selected aspects of diffusion and lean premix combustion modeling, predictions, observations and validated CFD results associated with the Solar Turbines Mars™ SoLoNOx combustor are presented. CO and NOx emission formation modeling details applicable to parametric CFD analysis in an industrial design environment are discussed. This effort culminated in identifying phenomena and methods of potentially further reducing NOx and CO emissions while improving engine operability in the Mars™ SoLoNOx combustion system. A potential explanation for the abrupt rise in CO formation observed in many gas turbine lean premix combustion systems is presented.

Coal-Water Slurry Testing of an Industrial Gas Turbine

1992 ◽  
Author(s):  
R. A. Wenglarz ◽  
C. Wilkes ◽  
R. C. Bourke ◽  
H. C. Mongia
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Water Injection ◽  
Department Of Energy ◽  
Combustion System ◽  
Hot Gas ◽  
Water Slurry ◽  
Coal Water Slurry ◽  
Burning Coal ◽  
Industrial Gas Turbine

This paper describes the first test of an industrial gas turbine and low emissions combustion system on coal-water-slurry fuel. The engine and combustion system have been developed over the past five years as part of the Heat Engines program sponsored by the Morgantown Energy Technology Center of the U.S. Department of Energy (DOE). The engine is a modified Allison 501-K industrial gas turbine designed to produce 3.5 MW of electrical power when burning natural gas or distillate fuel. Full load power output increases to approximately 4.9 MW when burning coal-water slurry as a result of additional turbine mass flow rate. The engine has been modified to accept an external staged combustion system developed specifically for burning coal and low quality ash-bearing fuels. Combustion staging permits the control of NOx from fuel-bound nitrogen while simultaneously controlling CO emissions. Water injection freezes molten ash in the quench zone located between the rich and lean zones. The dry ash is removed from the hot gas stream by two parallel cyclone separators. This paper describes the engine and combustor system modifications required for running on coal and presents the emissions and turbine performance data from the coal-water slurry testing. Included is a discussion of hot gas path ash deposition and planned future work that will support the commercialization of coal-fired gas turbines.

Managing Gas Turbine Combustion System Fuel Manifold Distress Through Ultrasonic Inspections and Calibrated Fracture Analyses

2017 ◽  
Author(s):  
Scott Keller ◽  
Afzal Pasha Mohammed ◽  
Khalid Oumejjoud
Keyword(s):  
Gas Turbine ◽  
Residual Life ◽  
Ultrasonic Inspection ◽  
Combustion System ◽  
Fuel Delivery ◽  
The Common ◽  
Support Housing ◽  
Industrial Gas Turbine ◽  
Lifecycle Management ◽  
Ray Methods

One of the common issues within the industrial gas turbine fleet is the susceptibility of a can-annular combustors’ fuel manifold cover (support housings) to develop embedded cracks. These cracks, located in the assembly joint of cover plates that create internal passages for fuel delivery to the combustion system, have enough of a driving force to propagate to the surface of the component. Once a crack propagates to the surface, gas has the potential to leak into the enclosure, posing a potential fire and safety risk. Furthermore, cracked fuel manifold covers are prone to increased NOx levels and excessive dynamics. Consequently, operators have the potential for a forced outage due to the failure of the fuel manifold. Currently, the existing solution is to replace the support housings with new or refurbished housings, with prior analyses requiring near perfect fusion. An ultrasonic inspection procedure has been developed to inspect a combustor’s fuel manifold cover for embedded cracks, which are not currently detectable with FPI or X-ray methods. Through this method, the amount of fusion in the assembly joint is readily obtained, including the ability to understand if the crack is partial-thickness or through-thickness. Parametric fracture analyses, utilizing experimental material test data calibrated to service-exposed components, are conducted to predict the residual life. Coupled with the engine operating data, including the use of cold- or heated-fuels, a recommendation for the remaining useful operation of the support housings can be provided. Ultimately, by completing the ultrasonic inspection and analysis on the support housing/fuel manifold, both the risk of an unplanned outage in the future and the lifecycle management cost to the operator is reduced.

Combustion Characteristics of Methane-CO2 Mixture and a Microturbine Cogeneration System Utilized Sewage Digester Gas

2007 ◽  
Author(s):  
Tadashi Kataoka ◽  
Teruyuki Nakajima ◽  
Takahiro Nakagawa ◽  
Nobuhiko Hamano ◽  
Saburo Yuasa
Keyword(s):  
Carbon Dioxide ◽  
Gas Turbine ◽  
Power Output ◽  
Gas Turbines ◽  
Combustion Efficiency ◽  
Stable Operation ◽  
Combustion System ◽  
Lean Burn ◽  
Peripheral Equipment ◽  
Cogeneration System

This paper describes an approach to utilize sewage digester gas as a fuel for gas turbines. Sewage digester gas is composed of about 60% methane and 39% carbon dioxide. To apply it as a gas turbine fuel requires optimizing the combustion system to improve the combustion efficiency, flame-holding characteristics, etc. This paper presents an approach whereby a mass-produced microturbine and its peripheral equipment can be converted for such application with a minimum of modification and without the use of extraordinary combustors. The approach is described whereby a recuperative cycle microturbine having rich-burn, quick-mix, lean-burn (RQL) combustor is started up with a high-Btu fuel and the fuel is switched to digester gas when the inlet-air has been preheated to 600K or higher. This approach has proven that reliable starting, stable operation from idling to the rated power output, and efficiency equivalent to that obtained with a high-Btu fuel, can be achieved by the microturbine utilizing sewage digester gas.

Acoustic Resonances of an Industrial Gas Turbine Combustion System

2000 ◽  
Author(s):  
S. Hubbard ◽  
A. P. Dowling
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Acoustic Waves ◽  
Low Frequency ◽  
Operating Conditions ◽  
Combustion System ◽  
Resonant Frequencies ◽  
Bulk Mode ◽  
Acoustic Resonances ◽  
Industrial Gas Turbine

A theory is developed to describe low frequency acoustic waves in the complicated diffuser/combustor geometry of a typical industrial gas turbine. This is applied to the RB211-DLE geometry to give predictions for the frequencies of the acoustic resonances at a range of operating conditions. The main resonant frequencies are to be found around 605 Hz (associated with the plenum) and around 461 Hz and 823 Hz (associated with the combustion chamber), as well as one at around 22 Hz (a bulk mode associated with the system as a whole).

Structural Design and High-Pressure Test of a Ceramic Combustor for 1500°C Class Industrial Gas Turbine

1997 ◽  
Vol 119 (3) ◽  
pp. 506-511 ◽  
Author(s):  
I. Yuri ◽  
T. Hisamatsu ◽  
K. Watanabe ◽  
Y. Etori
Keyword(s):  
Fracture Toughness ◽  
High Pressure ◽  
Gas Turbine ◽  
Structural Design ◽  
Metal Structure ◽  
Combustion Efficiency ◽  
Test Results ◽  
Industrial Gas Turbine ◽  
Hybrid Ceramic ◽  
Load Conditions

A ceramic combustor for a 1500°C, 20 MW class industrial gas turbine was developed and tested. This combustor has a hybrid ceramic/metal structure. To improve the durability of the combustor, the ceramic parts were made of silicon carbide (SiC), which has excellent oxidation resistance under high-temperature conditions as compared to silicon nitride (Si3N4), although the fracture toughness of SiC is lower than that of Si3N4. Structural improvements to allow the use of materials with low fracture toughness were made to the fastening structure of the ceramic parts. Also, the combustion design of the combustor was improved. Combustor tests using low-Btu gaseous fuel of a composition that simulated coal gas were carried out under high pressure. The test results demonstrated that the structural improvements were effective because the ceramic parts exhibited no damage even in the fuel cutoff tests from rated load conditions. It also indicated that the combustion efficiency was almost 100 percent even under part-load conditions.

Description of a 9000 HP Single Shaft Gas Turbine

1960 ◽  
Author(s):  
O. C. Schoeppner
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Turbine Rotor ◽  
Decisive Factor ◽  
Combustion System ◽  
Test Program ◽  
Important Place ◽  
Prime Movers ◽  
Industrial Gas Turbine

Low first cost and little need for maintenance assure the industrial gas turbine an important place for many applications where the lower thermal efficiency as compared with other prime movers is not a decisive factor. The simplicity of the gas turbine finds its best expression in the compact integrated single shaft design featuring a single compressor-turbine rotor supported in two bearings, the whole including the combustion system being contained in a common casing structure. The recognized need for simplicity together with reliability has been the main consideration in the design of the unit presented in the following description. At present, an intensive test program is under way and it is expected that the new Clark gas turbine will soon be ready for installation.

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