Catalytic combustion enabling technologies development program for industrial gas turbine systems. Final report

2002 ◽  
Author(s):  
S. Etemad ◽  
W. Pfefferle ◽  
L. Smith ◽  
H. Karim ◽  
M. Castaldi ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Catalytic Combustion ◽  
Development Program ◽  
Final Report ◽  
Enabling Technologies ◽  
Industrial Gas Turbine

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.

Development of FT9 Marine Gas Turbine

1981 ◽  
Author(s):  
D. A. Groghan ◽  
C. L. Miller
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
System A ◽  
On Line ◽  
Condition Monitoring System ◽  
Industrial Gas Turbine ◽  
Engine Condition

The FT9 Marine Gas Turbine development program was initiated in August 1973 by the Naval Sea Systems Command to fulfill, in part, the requirement for a family of gas turbine engines ranging in power from 1000 to 30,000 hp. The FT9 satisfied the requirement to develop a 30,000 hp class marine gas turbine. The FT9 is a derivative of the Pratt & Whitney Aircraft JT9D engine, which powers Boeing 747, DC-10 and A300 aircraft, and of the FT4 industrial gas turbine engine. The FT9 specification also required development of an on-line engine condition monitoring system. A rigorous development test program showed the FT9 has met all specified U.S. Navy requirements and demonstrated its suitability for use in U.S. Navy combatant ships.

scholarly journals High-reliability gas turbine combined-cycle development program. Phase I. Final report

1980 ◽  
Author(s):  
R. E. Strong ◽  
D. J. Amos ◽  
K. H. Eagle ◽  
G. L. Francois
Keyword(s):  
Phase I ◽  
Gas Turbine ◽  
High Reliability ◽  
Development Program ◽  
Combined Cycle ◽  
Final Report

Development and Testing of a 333 Kilowatt Industrial Gas Turbine

2016 ◽  
Author(s):  
Jeffrey Armstrong ◽  
Christopher Bolin ◽  
Mohammed Ebrahim ◽  
Michael Carney
Keyword(s):  
Gas Turbine ◽  
Power Efficiency ◽  
Oil And Gas ◽  
Guide Vane ◽  
Development Program ◽  
Lessons Learned ◽  
Inlet Guide Vane ◽  
General Description ◽  
Engine Testing ◽  
Industrial Gas Turbine

The development of a derivative small industrial gas turbine, sometimes termed a “microturbine”, is described. The target markets were the oil and gas upstream and midstream markets, and combined heat and power applications. These applications defined the product objectives. A general description is presented of the baseline recuperated gas turbine from which the new gas turbine is derived. The new gas turbine is a 333kWe recuperated gas turbine with a modernized compressor, variable inlet guide vanes for improved part-power efficiency and emissions, and an improved hot-section. The applicability and advantages of the GT333S features are compared with the market requirements. The development program included compressor rig testing, inlet guide vane development and testing, and engine testing. For the new product, a large number of components remained unchanged from GT250S, including most of the drivetrain. This provided confidence that the reliability of the GT333S, based on the millions of successful operating hours accrued on the GT250S, would translate into good GT333S reliability and availability. Extensive factory testing was performed to demonstrate the robustness of the new engine. The final performance results showed that the gas turbine achieved the program objectives. Some lessons learned from the development program are described.

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.

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 Operational and Maintenance Experience of an Industrial Type 14-MW Gas Turbine

1977 ◽  
Author(s):  
H. Werner ◽  
S. Ekman ◽  
H. Boltshauser
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Jet Engine ◽  
Industrial Gas Turbine ◽  
Engine Development

The GT35, originally planned as a new step in the author’s jet engine development program, is a lightweight industrial gas turbine. This paper describes the operation, maintenance procedures, costs, problems and cures of several plants located in Sweden, Venezuela, Holland, Turkey and Algeria.

Catalytic Combustor Development for Ultra-Low Emissions Industrial Gas Turbines

1997 ◽  
Author(s):  
P. Dutta ◽  
D. K. Yee ◽  
R. A. Dalla Betta
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Catalytic Combustion ◽  
System Development ◽  
Technical Information ◽  
Development Program ◽  
Catalyst Design ◽  
Load Range ◽  
Catalytic Combustor ◽  
Substrate Temperatures

The goal of the Advanced Turbine Systems (ATS) program is to develop a high thermal efficiency industrial gas turbine with ultra-low emissions (<10 ppmv NOx, CO and UHC @ 15% O2) over the 50 to 100% load range. Catalytic combustion was chosen as an approach likely to meet ATS emissions goals. A subscale catalytic combustor development program was designed to develop a technical knowledge base for catalyst design (catalyst construction, length), performance (ignition, activity and emissions) and operating limitations (fuel-air turndown and sensitivity to combustor operating variables). A novel catalyst design with preferential catalyst coating to limit substrate temperatures was used in the tests. The catalytic combustor consists of a fuel-air premixer, catalytic reactor and a post-catalyst zone for completion of homogeneous gas phase reactions. In situ measurements of mean fuel concentrations at the exit of the premixer were completed to characterize fuel-air premixing levels. Performance of the catalyst was monitored through global emissions measurements at the exit of the post-catalyst combustor under simulated engine conditions, and measurement of catalyst substrate temperatures. Ultra-low emissions were achieved for relatively uniform fuel-air premixing (<10% peak to peak variation in fuel concentration) with higher inhomogeneities (>10% peak to peak variation) leading to either locally high or low substrate temperatures. Regions with low substrate temperatures led to high CO and UHC emissions. Modeling of post-catalyst homogeneous reactions using a standard stationary, one-dimensional, laminar premixed flame formulation showed good agreement with measurements. In short term tests, the catalysts showed the desired chemical activity and ability for multiple light-off. The subscale combustor development work provided the necessary technical information for full scale catalytic combustion system development for the ATS gas turbine.

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