scholarly journals Development and Shop Test Results of a New 25–35MW Class Gas Turbine MF-221

1996 ◽  
Author(s):  
K. Takeishi ◽  
H. Mori ◽  
K. Tsukagoshi ◽  
M. Takahama
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Axial Compressor ◽  
Combined Cycle ◽  
Load Test ◽  
Test Facility ◽  
Medium Size ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Cooling

Mitsubishi Heavy industries Ltd. developed a new high efficiency medium-size (25–35MW) gas turbine MF-221 to be used in a cogeneration plant. This gas turbine is an upscaled design of the MF-111 model, which has accumulated an operation experience of more than 1,020,000hrs. The improvement of performance and reliability was made possible by technology transfer from the latest 501F/701F gas turbine with respect to compressor and turbine aerodynamics, materials, coating and turbine cooling technology. The MF-221 has a base load rating of 30MW at 1250°C turbine inlet temperature. Its thermal efficiency is 32% and 45% for simple and combined cycle application, respectively. It consists of a single shaft, 17-stage axial compressor, 10 can-type combustors and a 3-stage axial turbine. The prototype engine has been tested in a full-load test facility at Takasago Machinery Works to confirm the efficiency and the reliability of all parts exposed to high temperatures.

Initial Operating Experience and Test Results of ABB’s Gas Turbine GT13E2

1995 ◽  
Author(s):  
M. Klohr ◽  
J. Schmidtke ◽  
S. Tschirren ◽  
P. Rihak
Keyword(s):  
Gas Turbine ◽  
Dynamic Pressure ◽  
Operating Experience ◽  
Combined Cycle ◽  
Test Facility ◽  
Vibration Velocity ◽  
Inlet Temperature ◽  
Test Results ◽  
Pressure System ◽  
Annular Combustor

On 20 October 1993, the first ABB GT13E2 gas turbine was put into operation. This 165 MW class gas turbine achieves 35,7% thermal efficiency in single cycle application and up to 54,3% (according ISO standard 3977, Annexe F) in a three pressure system. An optimised turbine and compressor design along with the increased turbine inlet temperature, lead to improved efficiency and electrical output. A new concept for the combustor aimed at meeting the increasing demands on gas turbine emissions. The GT13E2 is equipped with the new single annular combustor and 72 of the ABB EV double cone burners. The commissioning and testing of the first GT13E2 was carried out at the Kawasaki Gas Turbine Research Center (KGRC) in Sodegaura City near Tokyo, Japan. The gas turbine was assembled with various measurement systems to monitor static and dynamic pressure, gas and metal temperature, expansion, vibration, velocity and emissions. The facility will be used during a 15 year joint test program by ABB and Kawasaki Heavy Industries (KHI) to obtain a sound database of operating experience for further improvements of the GT13E2 gas turbine. Therefore, mid 1994 a second test phase was conducted and early 1995 a third test period is scheduled. In parallel, the 2nd and 3rd GT13E2’s were commissioned and tested at the Deeside Combined Cycle Power Plant near Chester, Great Britain. In November 1994, the 4th GT13E2 at Lage Weide was successfully commissioned. This paper describes the operating experience with the GT13E2 during the first commissioning and test phases at KGRC and Deeside. The design features, the test facility, the instrumentation, the commissioning and test results are presented and discussed.

scholarly journals High-Temperature Turbine Technology Readiness

1982 ◽  
Author(s):  
M. W. Horner ◽  
A. Caruvana
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Phase Ii ◽  
Combined Cycle ◽  
Technology Readiness ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet ◽  
Combined Cycle Plant ◽  
Gas Fuel

Final component and technology verification tests have been completed for application to a 2600°F rotor inlet temperature gas turbine. These tests have proven the capability of combustor, turbine hot section, and IGCC fuel systems and controls to operate in a combined cycle plant burning a coal-derived gas fuel at elevated gas turbine inlet temperatures (2600–3000°F). This paper presents recent test results and summarizes the overall progress made during the DOE-HTTT Phase II program.

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.

Development of an 8MW-Class High-Efficiency Gas Turbine, M7A-03

2007 ◽  
Author(s):  
Kazuhiko Tanimura ◽  
Naoki Murakami ◽  
Akinori Matsuoka ◽  
Katsuhiko Ishida ◽  
Hiroshi Kato ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
High Performance ◽  
High Efficiency ◽  
High Reliability ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Gas Temperature ◽  
Turbine Cooling ◽  
Distributed Power Generation

The M7A-03 gas turbine, an 8 MW class, single shaft gas turbine, is the latest model of the Kawasaki M7A series. Because of the high thermal efficiency and the high exhaust gas temperature, it is particularly suitable for distributed power generation, cogeneration and combined-cycle applications. About the development of M7A-03 gas turbine, Kawasaki has taken the experience of the existing M7A-01 and M7A-02 series into consideration, as a baseline. Furthermore, the latest technology of aerodynamics and cooling design, already applied to the 18 MW class Kawasaki L20A, released in 2000, has been applied to the M7A-03. Kawasaki has adopted the design concept for achieving reliability within the shortest possible development period by selecting the same fundamental engine specifications of the existing M7A-02 – mass air flow rate, pressure ratio, TIT, etc. However, the M7A-03 has been attaining a thermal efficiency of greater than 2.5 points higher and an output increment of over 660 kW than the M7A-02, by the improvement in aerodynamic performance of the compressor, turbine and exhaust diffuser, improved turbine cooling, and newer seal technology. In addition, the NOx emission of the combustor is low and the M7A-03 has a long service life. These functions make long-term continuous operation possible under various environmental restraints. Lower life cycle costs are achieved by the engine high performance, and the high-reliability resulting from simple structure. The prototype M7A-03 gas-turbine development test started in the spring of 2006 and it has been confirmed that performance, mechanical characteristics, and emissions have achieved the initial design goals.

Development of ODS Coating for High Temperature Turbine Components Using DED Additive Manufacturing

2018 ◽  
Author(s):  
Eric Chia ◽  
Bruce S. Kang ◽  
Min Zheng ◽  
Yang Li ◽  
Minking Chyu
Keyword(s):  
High Temperature ◽  
Additive Manufacturing ◽  
Gas Turbine ◽  
Thermally Grown Oxide ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Test Results ◽  
Dispersion Strengthening ◽  
Thermal Cycles

Current and future designs for advanced turbine systems, such as Integrated Gasification Combined Cycle (IGCC), advanced Natural Gas Combined Cycle (NGCC), and the emerging supercritical CO2 (SCO2) systems require increasing turbine inlet temperature (TIT), which is well beyond the substrate melting temperature. The well-known approach is coating the turbine blade with thermal barrier coatings (TBC) combined with internal cooling channel in the substrate. However, due to thermally grown oxide (TGO) and thermal expansion mismatch stresses, TBC spallation failure is a major concern. Furthermore, neither the ceramic coating layer nor the metallic bond coat in current TBC system can provide structural support to house the internal cooling channels. In this research, a method to fabricate high temperature protective structural coating on top of critical gas turbine components by additive manufacturing (AM) technique using oxide dispersion strengthening (ODS) metal powder is presented. A novel combined mechanochemical bonding (MCB) plus ball milling process is utilized to produce near spherical and uniformly alloyed ODS powders. AM-processed ODS coating by direct energy deposition (DED) method on MAR-247 substrate, with laser powers from 100W to 200W were carried out. The ODS coated samples were then subjected to thermal cyclic loadings for over 2200 cycles. For comparison, in our earlier studies, under the same cyclic testing condition, typical tested TBC coupons showed spallation failure after ∼400 cycles. Correlation of the measured ODS coating Young’s modulus using a unique non-destructive micro-indentation testing method with evolution of the ODS microstructures are studied to identify optimum AM processing parameters for best performance of the ODS samples. In particular, stability of secondary γ′ phase in the ODS coating after thermal cycles is analyzed. Test results revealed a thin steady durable alpha alumina oxide layer on the best performance ODS samples. After 2,200 thermal cycles, strong bonding at ODS/substrate interface is also maintained for most of the ODS coated samples. Test results also showed stable substrate microstructure due to the protective ODS coating even after 2,200 thermal cycles. These preliminary test results showed strong potential for applications of AM-assisted ODS coating on advanced gas turbine components.

The Performance Analysis of a Combined Power Plant Implementing Technologies for Enhancing Power and Efficiency

2015 ◽  
Author(s):  
Jumok Won ◽  
Changmin Son ◽  
Changju Kim
Keyword(s):  
Gas Turbine ◽  
Cooling System ◽  
Promising Result ◽  
Load Condition ◽  
Steam Injection ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Net Benefit ◽  
Turbine Cooling ◽  
The Difference

Combined Cycle Power (CCP) plant using Liquefied Natural Gas (LNG) plays a key role in electric supply including nuclear and coal power generation systems. There is growing demand for enhancing power and efficiency of existing CCP plants. Typically, the power reduction of gas turbine during summer can be recovered if gas turbine intake cooling system can be implemented in existing LNG based CCP plants. Possible approaches for power and efficiency enhancement are being widely studied in global gas turbine society. The present study aims to investigate net benefit of implementing selected technologies for enhancing power and efficiency of an existing LNG based CCP. For a comparative study, selected technologies such as (1) gas turbine intake cooling system, (2) wet cycle (steam injection), and (3) turbine cooling air precooling are implemented to Busan LNG based CCP plant, Republic of Korea. The complete CCP plant is modeled using Gatecycle and its validation against field operation data showed the differences in the generated power and efficiency at the base load condition within 0.5% and the difference in the turbine inlet temperature value less than 3%. Among the selected technologies, the wet cycle (steam injection) showed the most promising result. Its system composition is relatively simple in comparison to the other technologies. Furthermore, it is advantageous to use within a reasonable limit when higher power is required for peak demand of electric power.

Design and Validation of a Compressor for a New Generation of Heavy-Duty Gas Turbines

2007 ◽  
Author(s):  
F. Eulitz ◽  
B. Kuesters ◽  
F. Mildner ◽  
M. Mittelbach ◽  
A. Peters ◽  
...  
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Performance ◽  
High Efficiency ◽  
Forced Response ◽  
Combined Cycle ◽  
Test Facility ◽  
Primary Driver ◽  
Compressor Technology

Siemens H-Class. Siemens has developed the world-largest H-class Gas Turbine (SGT™) that sets unparalleled standards for high efficiency, low life cycle costs and operating flexibility. With a power output of 340+ MW, the SGT5–8000H gas turbine will be the primary driver of the new Siemens Combined Cycle Power Plant (SCC™) for the 50 Hz market, the SCC5–8000H, with an output of 530+ MW at more than 60% efficiency. After extensive lab and component testing, the prototype has been shipped to the power plant for an 18-month validation phase. In this paper, the compressor technology, which was developed for the Siemens H-class, is presented through its development and validation phases. Reliability and Availability. The compressor has been extensively validated in the Siemens Berlin Test Facility during consecutive engine test programs. All key parameters, such as mass flow, operating range, efficiency and aero mechanical behavior meet or exceed expectations. Six-sigma methodology has been exploited throughout the development to implement the technologies into a robust design. Efficiency. The new compressor technology applies the Siemens advanced aerodynamics design methodology based on the high performance airfoil (HPA) systematic which leads to broader operation range and higher efficiency than a standard controlled diffusion airfoil (CDA) design. Operational Flexibility. The compressor features an IGV and three rows of variable guide vanes for improved turndown capability and improved part load efficiency. Serviceability. The design has been optimized for serviceability and less complexity. Following the Siemens tradition, all compressor rotating blades can be replaced without rotor lift or destacking. Evolutionary Design Innovation. The compressor design incorporates the best features and experience from the operating fleets and technology innovation prepared through detailed research, analysis and lab testing in the past decade. The design tools are based on best practices from former Siemens KWU and Westinghouse with enhancements allowing for routine front-to-back compressor 3D CFD multistage analysis, unsteady blade row interaction, forced response analyses and aero-elastic analysis.

Investigation of the Bottoming Cycle for High Efficiency Combined Cycle Gas Turbine System With Supercritical Carbon Dioxide Power Cycle

2015 ◽  
Author(s):  
Seong Kuk Cho ◽  
Minseok Kim ◽  
Seungjoon Baik ◽  
Yoonhan Ahn ◽  
Jeong Ik Lee
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
High Efficiency ◽  
Waste Heat ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Power Cycle ◽  
Turbine Inlet ◽  
Steam Cycle

The supercritical CO2 (S-CO2) power cycle has been receiving attention as one of the future power cycle technology because of its compact configuration and high thermal efficiency at relatively low turbine inlet temperature ranges (450∼750°C). Thus, this low turbine inlet temperature can be suitable for the bottoming cycle of a combined cycle gas turbine because its exhaust temperature range is approximately 500∼600°C. The natural gas combined cycle power plant utilizes mainly steam Rankine cycle as a bottoming cycle to recover waste heat from a gas turbine. To improve the current situation with the S-CO2 power cycle technology, the research team collected various S-CO2 cycle layouts and compared each performance. Finally, seven cycle layouts were selected as a bottoming power system. In terms of the net work, each cycle was evaluated while the mass flow rate, the split flow rate and the minimum pressure were changed. The existing well-known S-CO2 cycle layouts are unsuitable for the purpose of a waste heat recovery system because it is specialized for a nuclear application. Therefore, the concept to combine two S-CO2 cycles was suggested in this paper. Also the complex single S-CO2 cycles are included in the study to explore its potential. As a result, the net work of the concept to combine two S-CO2 cycles was lower than that of the performance of the reference steam cycle. On the other hand, the cascade S-CO2 Brayton cycle 3 which is one of the complex single cycles was the only cycle to be superior to the reference steam cycle. This result shows the possibility of the S-CO2 bottoming cycle if component technologies become mature enough to realize the assumptions in this paper.

Development of a 20MW-Class High-Efficiency Gas Turbine L20A

2002 ◽  
Author(s):  
Takao Sugimoto ◽  
Katsushi Nagai ◽  
Masanori Ryu ◽  
Ryozo Tanaka ◽  
Takeshi Kimura ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Life Cycle Cost ◽  
High Efficiency ◽  
Axial Flow ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Gas Temperature ◽  
Cogeneration System ◽  
Flow Compressor

The L20A gas turbine is a newly developed 20 MW class single-shaft machine. With its high simple-cycle efficiency and high exhaust gas temperature, it is particularly suited for use in distributed power generation, cogeneration and combined cycle applications. A design philosophy has been adopted for the turbine which includes a high efficiency transonic axial-flow compressor with eight can-type combustors and a high inlet temperature of 1250°C. This results in a thermal efficiency of 35% and an overall thermal efficiency of 80% for cogeneration system. In addition, the NOx emissions from the combustor is low and the L20A has a long service life. These features permit long-term continuous operation under various environmental limitations. Due to the engine’s high efficiency and its low component totals, the lowest life cycle cost is achieved. Development testing has verified that the performance, the mechanical characteristics and the emission have satisfied the initial design goals. The engine has been in operation from November 2001 as the first operating unit in a co-generation system at Kawasaki Akashi Works.

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.

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