Low Emissions Combustor Development for an Industrial Gas Turbine to Utilize LCV Fuel Gas

1994 ◽  
Vol 116 (3) ◽  
pp. 559-566 ◽  
Author(s):  
G. J. Kelsall ◽  
M. A. Smith ◽  
M. F. Cannon
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Development Program ◽  
Calorific Value ◽  
Pollutant Emissions ◽  
Inlet Temperature ◽  
Second Phase ◽  
Fuel Gas ◽  
Topping Cycle ◽  
Industrial Gas Turbine

Advanced coal-based power generation systems such as the British Coal Topping Cycle offer the potential for high-efficiency electricity generation with minimum environmental impact. An important component of the Topping Cycle program is the gas turbine, for which development of a combustion system to burn low calorific value coal derived fuel gas, at a turbine inlet temperature of 1260°C (2300°F), with minimum pollutant emissions, is a key R&D issue. A phased combustor development program is underway burning low calorific value fuel gas (3.6-4.1 MJ/m3) with low emissions, particularly NOx derived from fuel-bound nitrogen. The first phase of the combustor development program has now been completed using a generic tubo-annular, prototype combustor design. Tests were carried out at combustor loading and Mach numbers considerably greater than the initial design values. Combustor performance at these conditions was encouraging. The second phase of the program is currently in progress. This will assess, initially, an improved variant of the prototype combustor operating at conditions selected to represent a particular medium sized industrial gas turbine. This combustor will also be capable of operating using natural gas as an auxiliary fuel, to suit the start-up procedure for the Topping Cycle. The paper presents the Phase 1 test program results for the prototype combustor. Design of the modified combustor for Phase 2 of the development program is discussed, together with preliminary combustion performance results.

scholarly journals Low Emissions Combustor Development for an Industrial Gas Turbine to Utilise LCV Fuel Gas

1993 ◽  
Author(s):  
G. J. Kelsall ◽  
M. A. Smith ◽  
M. F. Cannon
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Calorific Value ◽  
Development Programme ◽  
Pollutant Emissions ◽  
Inlet Temperature ◽  
Second Phase ◽  
Fuel Gas ◽  
Topping Cycle ◽  
Industrial Gas Turbine

Advanced coal based power generation systems such as the British Coal Topping Cycle offer the potential for high efficiency electricity generation with minimum environmental impact. An important component of the Topping Cycle programme is the gas turbine, for which development of a combustion system to burn low calorific value coal derived fuel gas, at a turbine inlet temperature of 1260°C (2300 F), with minimum pollutant emissions, is a key R&D issue. A phased combustor development programme is underway burning low calorific value fuel gas (3.6–4.1 MJ/m3) with low emissions, particularly NOx derived from fuel bound nitrogen. The first phase of the combustor development programme has now been completed using a generic tubo-annular, prototype combustor design. Tests were carried out at combustor loading and mach numbers considerably greater than the initial design values. Combustor performance at these conditions was encouraging. The second phase of the programme is currently in progress. This will assess, initially, an improved variant of the prototype combustor operating at conditions selected to represent a particular medium sized industrial gas turbine. This combustor will also be capable of operating using natural gas as an auxiliary fuel, to suit the start-up procedure for the Topping Cycle. The paper presents the Phase 1 test programme results for the prototype combustor. Design of the modified combustor for Phase 2 of the development programme is discussed, together with preliminary combustion performance results.

scholarly journals Combustion of LCV Coal Derived Fuel Gas for High Temperature, Low Emissions Gas Turbines in the British Coal Topping Cycle

1991 ◽  
Author(s):  
G. J. Kelsall ◽  
M. A. Smith ◽  
H. Todd ◽  
M. J. Burrows
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Calorific Value ◽  
Pollutant Emissions ◽  
Inlet Temperature ◽  
Outlet Temperature ◽  
Combustion System ◽  
Fuel Gas ◽  
Gas Turbine Combustion ◽  
Topping Cycle

Advanced coal based power generation systems such as the British Coal Topping Cycle offer the potential for high efficiency electricity generation with minimum environmental impact. An important component of the Topping Cycle programme is the development of a gas turbine combustion system to burn low calorific value (3.5–4.0 MJ/m3 wet gross) coal derived fuel gas, at a turbine inlet temperature of 1260°C, with minimum pollutant emissions. The paper gives an overview of the British Coal approach to the provision of a gas turbine combustion system for the British Coal Topping Cycle, which includes both experimental and modelling aspects. The first phase of this programme is described, including the design and operation of a low-NOx turbine combustor, operating at an outlet temperature of 1360°C and burning a synthetic low calorific value (LCV) fuel gas, containing 0 to 1000 ppmv of ammonia. Test results up to a pressure of 8 bar are presented and the requirements for further combustor development outlined.

scholarly journals Development of an LCV Fuel Gas Combustor for an Industrial Gas Turbine

1997 ◽  
Author(s):  
Douglas R. Constant ◽  
D. Mark Bevan ◽  
Michael F. Cannon ◽  
Gregory J. Kelsall
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Calorific Value ◽  
Pollutant Emissions ◽  
Performance Tests ◽  
Fuel Gas ◽  
Design Characteristics ◽  
Phased Development ◽  
Industrial Gas Turbine ◽  
Power Generation Systems

Advanced coal based power generation systems, such as the Air Blown Gasification Cycle (ABGC), offer the potential for high efficiency, electricity generation with minimum environmental impact. An important component of the ABGC development is the gas turbine combustion system. It must bum low calorific value (LCV) coal derived fuel gas, at high turbine inlet temperatures with minimum pollutant emissions. A phased development programme has been completed burning LCV fuel gas (3.6–4.1 MJ/m3) with low emissions, particularly NOx derived from fuel bound nitrogen. Performance tests were carried out on a generic tubo-annular, prototype combustor, at Mach numbers generally lower than those typical to engine applications, with encouraging results. Five design variants, operating at conditions selected to represent a particular medium sized industrial gas turbine each returned an improvement in combustor performance. A further five variants were investigated to establish which design characteristics and operating parameters most affected NOx emissions.

Summary of CGT302 Ceramic Gas Turbine Research and Development Program

2000 ◽  
Author(s):  
Isashi Takehara ◽  
Tetsuo Tatsumi ◽  
Yoshihiro Ichikawa
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
High Efficiency ◽  
Development Program ◽  
Pollutant Emissions ◽  
Inlet Temperature ◽  
Term Operation ◽  
Ceramic Components

The Japanese Ceramic Gas Turbine (CGT) research and development program (FY1988–1998) as a part of the New Sunshine Project funded by the Ministry of International Trade and Industry (MITI) was completed in March 1999. Kawasaki Heavy Industries, Ltd. (KM) participated in this research program from the beginning and developed a twin-shaft CGT with a recuperator, designated as the “CGT302”. The purposes of this program were: 1) to achieve both a high efficiency and low pollutant emissions level using ceramic components, 2) to prove a multi-fuel capability to be used in co-generation systems, and 3) to demonstrate long-term operation. The targets of this program were: i) to achieve a thermal efficiency of over 42% at a turbine inlet temperature (TIT) of 1350°C, ii) to keep its emissions within the regulated value by the law, and iii) to demonstrate continuous operation for more than a thousand hours at 1200°C TIT. The CGT302 has successfully attained its targets. In March 1999 the CGT302 recorded 42.1% thermal efficiency, and 31.7 ppm NOx emissions (O2 = 16%) at 1350°C TIT. At this time it had also accumulated over two thousand hours operation at 1200°C. In this paper, we summarize the development of the CGT302.

Summary of CGT302 Ceramic Gas Turbine Research and Development Program

2002 ◽  
Vol 124 (3) ◽  
pp. 627-635 ◽  
Author(s):  
I. Takehara ◽  
T. Tatsumi ◽  
Y. Ichikawa
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
High Efficiency ◽  
Development Program ◽  
Pollutant Emissions ◽  
Inlet Temperature ◽  
Term Operation ◽  
Ceramic Components

The Japanese ceramic gas turbine (CGT) research and development program (FY1988-1998) as a part of the New Sunshine Project funded by the Ministry of International Trade and Industry (MITI) was completed in March 1999. Kawasaki Heavy Industries, Ltd. (KHI) participated in this research program from the beginning and developed a twin-shaft CGT with a recuperator, designated as the “CGT302.” The purposes of this program were (1) to achieve both a high efficiency and low pollutant emissions level using ceramic components, (2) to prove a multifuel capability to be used in cogeneration systems, and (3) to demonstrate long-term operation. The targets of this program were (i) to achieve a thermal efficiency of over 42 percent at a turbine inlet temperature (TIT) of 1350°C, (ii) to keep its emissions within the regulated value by the law, and (iii) to demonstrate continuous operation for more than a thousand hours at 1200°C TIT. The CGT302 has successfully attained its targets. In March 1999 the CGT302 recorded 42.1 percent thermal efficiency, and 31.7 ppm NOx emissions (O2=16 percent) at 1350°C TIT. At this time it had also accumulated over 2000 hours operation at 1200°C. In this paper, we summarize the development of the CGT302.

Analysis of Intermediate Temperature Combined Cycles With a Carbon Dioxide Topping Cycle

2008 ◽  
Author(s):  
R. Chacartegui ◽  
D. Sa´nchez ◽  
F. Jime´nez-Espadafor ◽  
A. Mun˜oz ◽  
T. Sa´nchez
Keyword(s):  
Carbon Dioxide ◽  
Power Plant ◽  
Gas Turbine ◽  
High Efficiency ◽  
Solar Power ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Pressure Drops ◽  
Combined Cycles ◽  
Topping Cycle

The development of high efficiency solar power plants based on gas turbine technology presents two problems, both of them directly associated with the solar power plant receiver design and the power plant size: lower turbine intake temperature and higher pressure drops in heat exchangers than in a conventional gas turbine. To partially solve these problems, different configurations of combined cycles composed of a closed cycle carbon dioxide gas turbine as topping cycle have been analyzed. The main advantage of the Brayton carbon dioxide cycle is its high net shaft work to expansion work ratio, in the range of 0.7–0.85 at supercritical compressor intake pressures, which is very close to that of the Rankine cycle. This feature will reduce the negative effects of pressure drops and will be also very interesting for cycles with moderate turbine inlet temperature (800–1000 K). Intercooling and reheat options are also considered. Furthermore, different working fluids have been analyzed for the bottoming cycle, seeking the best performance of the combined cycle in the ranges of temperatures considered.

scholarly journals Study on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine

1993 ◽  
Author(s):  
S. Amagasa ◽  
K. Shimomura ◽  
M. Kadowaki ◽  
K. Takeishi ◽  
H. Kawai ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
High Efficiency ◽  
Development Program ◽  
Test Results ◽  
Directionally Solidified ◽  
Barrier Coating ◽  
Turbine Vane ◽  
Nickel Base ◽  
Industrial Gas Turbine

This paper describes the summary of a three year development program for the 1st stage stationary vane and rotating blade for the next generation, 1500°C Class, high efficiency gas turbine. In such a high temperature gas turbine, the 1st turbine vane and blade are the most important hot parts. Full coverage film cooling (FCFC) is adopted for the cooling scheme, and directionally solidified (DS) nickel base super-alloy and thermal barrier coating (TBC) will be used to prolong the creep and thermal fatigue life. The concept of the cooling configuration, fundamental cascade test results and material test results will be presented.

scholarly journals Development of 300 kW Class Ceramic Gas Turbine (CGT302)

1995 ◽  
Author(s):  
Kozi Nishio ◽  
Junzo Fujioka ◽  
Tetsuo Tatsumi ◽  
Isashi Takehara
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Iso Standard ◽  
Current State ◽  
Ceramic Components

With the aim of achieving higher efficiency, lower pollutant emissions, and multi-fuel capability for small to medium-sized gas turbine engines for use in co-generation systems, a ceramic gas turbine (CGT) research and development program is being promoted by the Japanese Ministry of International Trade and Industry (MITI) as a part of its “New Sunshine Project”. Kawasaki Heavy Industries (KHI) is participating in this program and developing a regenerative two-shaft CGT (CGT302). In 1993, KHI conducted the first test run of an engine with full ceramic components. At present, the CGT302 achieves 28.8% thermal efficiency at a turbine inlet temperature (TIT) of 1117°C under ISO standard conditions and an actual TIT of 1250°C has been confirmed at the rated speed of the basic CGT. This paper consists of the current state of development of the CGT302 and how ceramic components are applied.

scholarly journals Experimental Evaluation of a Two-Stage Slagging Combustor Design for a Coal-Fueled Industrial Gas Turbine

1992 ◽  
Author(s):  
L. H. Cowell ◽  
R. T. LeCren
Keyword(s):  
Gas Turbine ◽  
Combustion Zone ◽  
Combustion Process ◽  
Coal Ash ◽  
Pollutant Emissions ◽  
Test Facility ◽  
Inlet Temperature ◽  
Water Mixture ◽  
Test Results ◽  
Industrial Gas Turbine

A full-size combustor for a coal-fueled industrial gas turbine engine has been tested to evaluate combustion performance prior to integration with an industrial gas turbine. The design is based on extensive work completed through one-tenth scale combustion tests. Testing of the combustion hardware is completed with a high pressure air supply in a combustion test facility at the Caterpillar Technical Center. The combustor is a two-staged, rich-lean design. Fuel and air are introduced in the primary combustion zone where the combustion process is initiated. The primary zone operates in a slagging mode inertially removing coal ash from the gas stream. Four injectors designed for coal-water mixture (CWM) atomization are used to introduce the fuel and primary air. In the secondary combustion zone additional air is injected to complete the combustion process at fuel-lean conditions. The secondary zone also serves to reduce the gas temperatures exiting the combustor. The combustor has operated at test pressures of 7 bars with 600K inlet temperature. Tests have been completed to set the air flow split and to map the performance of the combustor as characterized by pollutant emissions, coal ash separation, and temperature profile. Test results with a comparison to subscale test results are discussed. The test results have indicated that the combustor operates at combustion efficiencies above 98% and with pollutant emissions below design goals.

Field and Application Experience of the Titan 130 Industrial Gas Turbine

2001 ◽  
Author(s):  
George Rocha ◽  
Rainer Kurz
Keyword(s):  
Gas Turbine ◽  
Development Strategy ◽  
High Performance ◽  
High Efficiency ◽  
Electrical Power ◽  
Field Evaluation ◽  
Operating Conditions ◽  
Pollutant Emissions ◽  
Evaluation Program ◽  
Industrial Gas Turbine

The two-shaft Titan 130 industrial gas turbine was introduced into commercial service in 1998 and has gained field experience in mechanical-drive and compressor-set applications. A single-shaft configuration is also available for electrical power generation applications. The 14-MW class two-shaft engine is nominally rated at 19,500 hp with a simple-cycle efficiency of more than 35% at ISO operating conditions. It is available with two combustor options: a dry, low-pollutant emissions combustion system featuring Solar’s proven SoLoNOx technology or a diffusion-flame type combustor adapted from Solar’s proven Mars gas turbine. The Titan 130 gas turbine design is an aerodynamic scale of the existing Taurus 70 product. The unit features a modified Mars air compressor and turbine section components directly scaled from the Taurus 70, resulting in a low-risk product design well-suited for industrial service applications. A major element of the development strategy included an extended field evaluation trial in actual operating conditions to demonstrate overall product durability. The first Titan 130 mechanical-drive package was placed into service at a natural gas pipeline compressor station and successfully completed a planned 8000-hour field evaluation program. Extensive inspection and operating data have been evaluated and the unit continues to operate in normal commercial service. A mechanical-drive package requires the successful marriage between the driver and the driven equipment. Most applications require a combination of high efficiency and high performance flexibility. Emphasis was placed on providing excellent gas compressor coverage for this product. The successful application of such a compression system is discussed and supported by site test data. This paper provides details of the Titan 130 field evaluation program, design enhancements and typical compressor set application performance characteristics.

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