Water-Cooled Gas Turbine Technology Development: Fuels Flexibility

1979 ◽  
Author(s):  
M. W. Horner ◽  
W. H. Day ◽  
D. P. Smith ◽  
A. Cohn
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Development Program ◽  
Open Circuit ◽  
Model Verification ◽  
Small Scale ◽  
Water Cooling ◽  
Gas Temperature ◽  
Pressurized Water ◽  
Early Results

A continuing technology development program initiated by General Electric (GE) in the early 1960s and joined by the Electric Power Research Institute (EPRI) in 1974 is successfully resolving potential barrier problems in the development of water cooled turbines. Early work by GE Corporate Research and Development demonstrated the feasibility of closed circuit, pressurized water-cooling of stationary nozzles (vanes), and of open circuit, unpressurized water-cooling of rotating buckets (blades). A small-scale turbine was designed, fabricated, and operated at a gas temperature of 2850 F (1565 C) at 16 atm, with surface metal temperatures less than 1000 F (540 C). Early results from the EPRI sponsored Water-Cooled Gas Turbine Development Programs were presented at the 1978 Gas Turbine Conference (Report #ASME 78-GT-72). This paper reports more recent results, obtained between mid-1977 and mid-1978. Significant progress has been made in a number of areas: (a) water-cooled nozzle and bucket design and fabrication, (b) corrosion kinetics model verification and testing, (c) partially filled internal channel bucket heat transfer testing, and (d) stationary to rotating water transfer and collection testing. Results to date are encouraging with regard to the application of water-cooled turbine components to achieve improved reliability and fuels flexibility at increased turbine firing temperatures.

Development of a Water-Cooled Gas Turbine

1978 ◽  
Author(s):  
M. W. Horner ◽  
W. H. Day ◽  
D. P. Smith ◽  
A. Cohn
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Pressure Ratio ◽  
Development Program ◽  
Combined Cycle ◽  
Small Scale ◽  
Performance Curves ◽  
Basic Technology ◽  
Gas Fuel ◽  
Turbine Design

Development of water-cooled gas turbine technology was begun at General Electric in the early 1960’s, and by the early 1970’s, a small-scale turbine had been operated to temperatures of 2850 F and 16 atm, with metal temperature less than 1000 F. The Water-Cooled Turbine Development Program was begun in 1974, funded by the Electric Power Research Institute, to do preliminary design on a utility-size gas turbine using water cooling and to do basic technology development to address the problem areas. This paper presents the results of the program, including descriptions of the test hardware and data on phenomena, such as corrosion, erosion, heat transfer, and water collection. Cycle analysis results are presented for two potential combined cycle configurations: (a) one using low-Btu coal gas fuel, and (b) one using a heavy liquid fuel. Summary performance curves are given showing the effect of changes of pressure ratio and firing temperature. Methods of improving the baseline cycle and their effect on baseline performance which are judged most promising are also given on the performance curves. Turbine design features to achieve low component metal surface temperatures for increased fuels flexibility are given with particular emphasis to the first-stage nozzles and buckets. Fundamental development testing needs have been identified and programs have been put into place to bring the water-cooled turbine to a point where a full-size water-cooled turbine can be built. Descriptions of the development test facilities, task descriptions, test plans and /or test results are given for eight tasks.

scholarly journals Current Status of Ceramic Gas Turbine (CGT302)

1998 ◽  
Author(s):  
Hirotake Kobayashi ◽  
Tetsuo Tatsumi ◽  
Takashi Nakashima ◽  
Isashi Takehara ◽  
Yoshihiro Ichikawa
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Technology Development ◽  
Development Program ◽  
Point Of View ◽  
Current Status ◽  
Fiscal Year ◽  
Inlet Temperature ◽  
Development Organization ◽  
New Energy

In Japan, from the point of view of energy saving and environmental protection, a 300kW Ceramic Gas Turbine (CGT) Research and Development program started in 1988 and is still continuing as a part of “the New Sunshine Project” promoted by the Ministry of International Trade and Industry (MITT). The final target of the program is to achieve 42% thermal efficiency at 1350°C of turbine inlet temperature (TIT) and to keep NOx emissions below present national regulations. Under contract to the New Energy and Industrial Technology Development Organization (NEDO), Kawasaki Heavy Industries, Ltd. (KHI) has been developing the CGT302 with Kyocera Corporation and Sumitomo Precision Products Co., Ltd. By the end of the fiscal year 1996, the CGT302 achieved 37.0% thermal efficiency at 1280°C of TIT. In 1997, TIT reached 1350°C and a durability operation for 20 hours at 1350°C was conducted successfully. Also fairly low NOx was proved at 1300°C of TIT. In January 1998, the CGT302 has achieved 37.4% thermal efficiency at 1250°C TIT. In this paper, we will describe our approaches to the target performance of the CGT302 and current status.

AGT101 Advanced Gas Turbine Technology Update

1986 ◽  
Author(s):  
G. L. Boyd ◽  
J. R. Kidwell ◽  
D. M. Kreiner
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Development Program ◽  
Turbine Rotor ◽  
Test Time ◽  
Inlet Temperature ◽  
Metal Foil ◽  
Steady State Operation ◽  
Full Speed ◽  
Engine Testing

The Garrett/Ford Advanced Gas Turbine Technology Development Program, designated AGT101, has made significant progress during 1985 encompassing ceramic engine and ceramic component testing. Engine testing has included full speed operation to 100,000 rpm and 1149C (2100F) turbine inlet temperature, initial baseline performance mapping and ceramic combustor start and steady state operation. Over 380 hours of test time have been accumulated on four development engines. High temperature foil bearing coatings have passed rig test and a thick precious metal foil coating selected for engine evaluation. Ceramic structures have been successfully rig tested at 1371C (2500F) for over 27 hours. Interface compatibility testing conducted during these runs indicate RBSN-to-RBSN or SASC-to-SASC result in “sticking” — however, RBSN-to-SASC in either planar or line contact show no evidence of sticking. Ceramic combustor rig tests have demonstrated acceptable lightoffs using either a conventional ignitor or a commercially available glow plug. Operation to 1371C (2500F) combustor discharge temperatures have also been demonstrated. Ceramic turbine rotor fabrication efforts have continued at ACC and Ford. Kyocera and NGK-Locke also have been working on the rotor. Several rotors have been received and are currently undergoing final machining and qualification tests. Testing of the all-ceramic AGT101 engine is currently scheduled for late 1985.

Development of 300kW Class Ceramic Gas Turbine (CGT303)

1994 ◽  
Author(s):  
Issel Ohhashi ◽  
Sadao Arakawa
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Maximum Output Power ◽  
Development Program ◽  
Maximum Output ◽  
Power Generator ◽  
Construction Machinery ◽  
Development Organization ◽  
New Energy ◽  
Ceramic Components

CCT303 is a two-shaft regenerative ceramic gas turbine with rotary heat exchangers for the purpose of mobile power generator. It is also widely adaptable for industrial machinery and construction machinery as well. The development program of CGT303 is funded by New Energy and Industrial Technology Development Organization (NEDO). The maximum output power of 300kW and thermal efficiency of 42% at TiT 1350C are the objectives of this development. The high TiT requires for the material of all gas passage components to use ceramics which are designed appropriately to keep sufficient strength by using sophisticated computer analysis. Hot spin tests on ceramic turbine rotors and thermal shock tests on stationary ceramic components have been carried out to prove their strength. The paper covers the design concept of CGT303 and results of analysis.

Simulation Model and Experimental Validation of a CHP Plant With Micro Gas Turbine

2012 ◽  
Author(s):  
Marco Badami ◽  
Mauro Ferrero ◽  
Armando Portoraro
Keyword(s):  
Simulation Model ◽  
Gas Turbine ◽  
Small Scale ◽  
Gas Temperature ◽  
Data Set ◽  
Micro Gas Turbine ◽  
Limit Value ◽  
Partial Load ◽  
Main Components ◽  
Energy And Momentum

The paper deals with a simulation model, developed in Matlab Simulink®, of a small-scale Combined Heat and Power (CHP) plant based on a recuperated micro gas turbine (mGT). A minimum data set, mainly obtainable from datasheets, was defined, that allows the model to simulate different mGT plants in the small-scale range with a good accuracy. The model implements the mass, energy and momentum equations of the main components of the power plant. A double control system has also been developed, with the aim of maintaining the rotational speed of the turbine /compressor assembly at the nominal fixed value, and at limiting the Exhaust Gas Temperature (EGT) below the limit value. The model has been validated by means of experimental data obtained from a commercial mGT (100 kWel, 170 kWth), installed at the Politecnico di Torino, whose energetic characterization has been performed both at rated and at partial load conditions. The layout and the characteristics of the measurement system are also described in the paper.

Coal Fueled Aero-Derivative Gas Turbine: Design Approach

1988 ◽  
Author(s):  
M. W. Horner ◽  
P. E. Sabla ◽  
S. G. Kimura
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Development Program ◽  
Small Scale ◽  
Water Mixture ◽  
Coal Fuel ◽  
Cost Of Energy ◽  
Annular Combustor ◽  
Environmentally Sound ◽  
Turbine Design

The direct use of coal as a gas turbine fuel offers the opportunity to burn coal in an environmentally sound manner at a competitive cost of energy. A development program is underway to verify the feasibility of using coal water mixture to fuel an aero-derivative gas turbine. This paper presents the overall program approach, required gas turbine design modifications, and reports the results from small-scale combustor test facilities. The GE LM500 gas turbine was selected for this program because of its high efficiency and size, which is appropriate for transportation and cogeneration markets. The LM500 gas turbine power system design will be modified to accommodate coal fuel and any required emissions control devices. The design for the modified annular combustor is complete and preparations for coal fired tests of a 140 degree annular sector combustor are in progress. The combustor design and test development are being supported by a component test program with a One Nozzle Segment Combustor and a single can combustor LM500 Turbine Simulator. These test facilities are providing results on coal water mixture handling and fuel nozzle design, air staging requirements, component metal temperatures, combustor temperature performance, ash deposition rates, and emissions abatement for NOx, SOx, and particulates.

Advanced Hydrogen Turbine Development Update

2012 ◽  
Author(s):  
Tim Bradley ◽  
John Marra
Keyword(s):  
Gas Turbine ◽  
System Integration ◽  
Technology Development ◽  
Development Program ◽  
Combined Cycle ◽  
Department Of Energy ◽  
Plant Performance ◽  
Materials Testing ◽  
Development Effort ◽  
Phase 2

Siemens Energy, Inc. was awarded a contract by the U.S. Department of Energy for the first two phases of the Advanced Hydrogen Turbine Development Program. The 3-Phase, multi-year program goals are to develop an advanced syngas, hydrogen and natural gas fired gas turbine fully integrated into coal-based Integrated Gasification Combined Cycle (IGCC) plants. The program goals include demonstrating: • A 3–5% point improvement in combined cycle efficiency above the baseline, • 20–30% reduction in combined cycle capital cost • Emissions of 2 ppm NOx @ 15% O2 by 2015. Siemens is currently well into Phase 2 of the program and has made significant progress in several areas. This includes the ability to attain the 2015 Turbine Program performance goals by developing component and systems level technologies, developing and implementing validation test plans for these systems and components, performing validation testing of component technologies, and performance demonstration through system studies. Siemens and the Advanced Hydrogen Turbine Program received additional funds from the American Recovery and Reinvestment Act (ARRA) in 2010. The additional funding serves to supplement budget shortfalls in the originally planned spend rate. The development effort has focused on engine cycles, combustion technology development and testing, turbine aerodynamics/cooling, modular component technology, materials/coatings technologies and engine system integration/flexibility considerations. High pressure combustion testing continues with syngas and hydrogen fuels on a modified premixed combustor. Advanced turbine airfoil concept testing continues. Novel manufacturing techniques were developed that allow for advanced castings and faster time to market capabilities. Materials testing continues and significant improvements were made in lifing for Thermal Barrier Coatings (TBC’s) at increased temperatures over the baseline. Studies were conducted on gas turbine/IGCC plant integration, fuel dilution effects, varying air integration, plant performance and plant emissions. The results of these studies and developments provide a firm platform for completing the advanced Hydrogen Turbine technologies development in Phase 2.

Final Report of the Key Technology Development Program for a Next-Generation High-Temperature Gas Turbine

1997 ◽  
Vol 119 (3) ◽  
pp. 617-623 ◽  
Author(s):  
M. Sato ◽  
Y. Kobayashi ◽  
H. Matsuzaki ◽  
S. Aoki ◽  
Y. Tsukuda ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Technology Development ◽  
Development Program ◽  
Combined Cycle ◽  
Final Report ◽  
Next Generation ◽  
Key Technologies ◽  
Low Nox Combustion ◽  
System 2

There is a strong demand for efficient and clean power-generating systems to meet recent energy-saving requirements and environmental regulations. A combined cycle power plant is one of the best solutions to the above [1]. Tohoku Electric Power Co., Inc., and Mitsubishi Heavy Industries, Ltd., have jointly developed three key technologies for a next-generation 1500°C class gas turbine. The three key technologies consist of: (1) high-temperature low-NOx combustion system. (2) row 1 turbine vane and blade with advanced cooling schemes, and (3) advanced heat-resistant materials; (2) and (3) were verified by HTDU (High Temperature Demonstration Unit). This paper describes the results of the above-mentioned six-year joint development.

scholarly journals Development of the AGT101 Regenerator Seals

1987 ◽  
Author(s):  
C. A. Fucinari ◽  
J. K. Vallance ◽  
C. J. Rahnke
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Dynamic Test ◽  
Development Program ◽  
Analytical Techniques ◽  
Gas Turbine Engine ◽  
Inlet Temperature ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Seal Design

The design and development of the regenerator seals used in the AGT101 gas turbine engine are described in this paper. The all ceramic AGT101 gas turbine engine was designed for 100 hp at 5:1 pressure ratio with 2500F (1371C) turbine inlet temperature. Six distinct phases of seal design were investigated experimentally and analytically to develop the final design. Static and dynamic test rig results obtained during the seal development program are presented. In addition, analytical techniques are described. The program objectives of reduced seal leakage, without additional diaphragm cooling, to 3.6% of total engine airflow and higher seal operating temperature resulting from the 2000F (1093C) inlet exhaust gas temperature were met.

scholarly journals A New Generation T56 Turboprop Engine

1984 ◽  
Author(s):  
W. L. McIntire
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Technology Development ◽  
Development Program ◽  
Cost Effective ◽  
Full Scale ◽  
Gas Generator ◽  
Turbine Engine ◽  
Engine Model ◽  
Turboprop Engine

The focus of the T56 Series IV turboprop engine development program is to improve power and fuel consumption through incorporation of demonstrated technology improvements while retaining the long term durability and cost effective design of the T56 family. The T56-A-427, the Navy Series IV derivative of the 5000 shp (3728.5 kW) class T56 turboprop engine, resulted from over ten years of technology development via Advanced Turbine Engine Gas Generator (ATEGG), Joint Technology Demonstrator Engine (JTDE), and advanced component programs at Allison Gas Turbine Operations. An example of government and industry cooperation to transfer advanced gas turbine technology is the Air Force Engine Model Derivative Program (EMDP). The initial full-scale demonstration in this program confirmed a 10–1/2% reduction in specific fuel consumption (sfc) and a power growth of 21% in the basic T56 frame. Continued early demonstrations and development by IR&D, Navy funds, and Allison discretionary funds showed a further sfc reduction to 13% and power increase of 28%. The full-scale development program is now underway to provide production engines in late 1986. Engines will be available for the Grumman E-2 and C-2 aircraft, with follow-on adaptions for Lockheed C-130/L100 and P-3 aircraft, and generator sets for DD 963, DDG 993, CG 47 and DDG 51 warships.

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