scholarly journals MS7001F Prototype Test Results

1989 ◽  
Author(s):  
D. E. Brandt
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Load Test ◽  
Test Results ◽  
Critical Temperatures ◽  
Prototype Test ◽  
Surge Margin ◽  
Pertinent Data ◽  
Post Test ◽  
Heavy Duty Gas Turbine

The MS7001F heavy–duty gas turbine has been designed utilizing advanced analytical methods and a substantial array of component tests. The integrity of the system required that the prototype unit, with its accessories, be rigorously tested under load. The factory load test was completed on May 18, 1988 after 387 hours and 134 start/stop cycles. The MS7001F prototype gas turbine was instrumented with more than 3000 pieces of instrumentation in order to record all critical temperatures, pressures, flows, strains, displacements, and other pertinent data. The load device was a modified MS7001E compressor, which also supplied the means by which the MS7001F prototype compressor’s pressure ratio was increased to provide for surge margin determination. Inlet throttling of the MS7001F compressor allowed for full firing temperature operation, at reduced load. The results of this factory prototype load test are reported in the paper as are observations made during post test teardown.

scholarly journals Gas turbine efficiency and ramp rate improvement through compressed air injection

2020 ◽  
pp. 095765092093208 ◽  
Author(s):  
Kamal Abudu ◽  
Uyioghosa Igie ◽  
Orlando Minervino ◽  
Richard Hamilton
Keyword(s):  
Gas Turbine ◽  
Guide Vane ◽  
Injection Rate ◽  
Inlet Guide Vane ◽  
Heavy Duty ◽  
Part Load ◽  
Surge Margin ◽  
Rate Improvement ◽  
Heavy Duty Gas Turbine ◽  
Variable Inlet Guide Vane

With the transition to more use of renewable forms of energy in Europe, grid instability that is linked to the intermittency in power generation is a concern, and thus, the fast response of on-demand power systems like gas turbines has become more important. This study focuses on the injection of compressed air to facilitate the improvement in the ramp-up rate of a heavy-duty gas turbine. The steady-state analysis of compressed airflow injection at part-load and full load indicates power augmentation of up to 25%, without infringing on the surge margin. The surge margin is also seen to be more limiting at part-load with maximum closing of the variable inlet guide vane than at high load with a maximum opening. Nevertheless, the percentage increase in the thermal efficiency of the former is slightly greater for the same amount of airflow injection. Part-load operations above 75% of power show higher thermal efficiencies with airflow injection when compared with other load variation approaches. The quasi-dynamic simulations performed using constant mass flow method show that the heavy-duty gas turbine ramp-up rate can be improved by 10% on average, for every 2% of compressor outlet airflow injected during ramp-up irrespective of the starting load. It also shows that the limitation of the ramp-up rate improvement is dominated by the rear stages and at lower variable inlet guide vane openings. The turbine entry temperature is found to be another restrictive factor at a high injection rate of up to 10%. However, the 2% injection rate is shown to be the safest, also offering considerable performance enhancements. It was also found that the ramp-up rate with air injection from the minimum environmental load to full load amounted to lower total fuel consumption than the design case.

Study on Combustor Outlet Temperature Field of Gas Turbine

2011 ◽  
Vol 138-139 ◽  
pp. 962-966 ◽  
Author(s):  
Kai Liu ◽  
Li Xu
Keyword(s):  
Experimental Study ◽  
Temperature Field ◽  
Gas Turbine ◽  
Reference Value ◽  
Test System ◽  
Outlet Temperature ◽  
Test Results ◽  
Heavy Duty ◽  
Pressure Test ◽  
Heavy Duty Gas Turbine

Experimental study on combustor outlet temperature field of heavy-duty gas turbine had been finished on high-pressure test system. Experimental results indicate: The OTDF is sensitive to diameter of dilution holes, and the RTDF is sensitive to location of dilution holes. The test results have important guiding significance and reference value to design, commission and working about the similar combustor.

Particulate and Sulfur Oxides Emissions From a 60-MW Heavy Duty Gas Turbine Burning No. 2 Distillate Fuel: Methods Development and Test Results

1982 ◽  
Author(s):  
G. L. Touchton ◽  
M. B. Hilt
Keyword(s):  
Sulfur Dioxide ◽  
Gas Turbine ◽  
Sulfur Oxides ◽  
Test Results ◽  
Heavy Duty ◽  
Methods Development ◽  
Fuel Ash ◽  
Heavy Duty Gas Turbine ◽  
Extreme Care ◽  
Distillate Fuel

A method for the measurement of particulate and sulfur oxides emissions has been developed and tested in the laboratory and the field. The development shows that changes in analysis methods, procedures, and materials are necessary in order to adapt standard USEPA methods to gas turbine conditions. In particular, extreme care must be taken to prevent the formation of pseudo particulate from sulfur dioxide. The field results demonstrate that a G.E. MS7001B emits less than 10 lbm/hr of total particulate if the fuel ash and sulfur content are suitably restricted.

A Performance Autopsy of Three Centrifugal Compressors for a Small Gas Turbine

2010 ◽  
Author(s):  
Colin Rodgers ◽  
Dan Brown
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Radial Flow ◽  
Pressure Ratio ◽  
Test Results ◽  
Design Features ◽  
Centrifugal Compressors ◽  
High Pressure Ratio ◽  
Flow Type ◽  
The One

Three 140mm tip diameter centrifugal compressors were designed and tested to determine the one exhibiting the best performance most suitable for eventual application to a small 60KW radial flow type gas turbine. The design features, and stage test results of these three moderately high pressure ratio impellers are presented, together with a comparison of their respective test and CFD computed performance maps.

Application of “H Gas Turbine” Design Technology to Increase Thermal Efficiency and Output Capability of the Mitsubishi M701G2 Gas Turbine

2005 ◽  
Vol 127 (2) ◽  
pp. 369-374 ◽  
Author(s):  
Y. Fukuizumi ◽  
J. Masada ◽  
V. Kallianpur ◽  
Y. Iwasaki
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Turbine Blades ◽  
Combined Cycle ◽  
Load Test ◽  
Air Cooling ◽  
Load Testing ◽  
Design Development

Mitsubishi completed design development and verification load testing of a steam-cooled M501H gas turbine at a combined cycle power plant at Takasago, Japan in 2001. Several advanced technologies were specifically developed in addition to the steam-cooled components consisting of the combustor, turbine blades, vanes, and the rotor. Some of the other key technologies consisted of an advanced compressor with a pressure ratio of 25:1, active clearance control, and advanced seal technology. Prior to the M501H, Mitsubishi introduced cooling-steam in “G series” gas turbines in 1997 to cool combustor liners. Recently, some of the advanced design technologies from the M501H gas turbine were applied to the G series gas turbine resulting in significant improvement in output and thermal efficiency. A noteworthy aspect of the technology transfer is that the upgraded G series M701G2 gas turbine has an almost equivalent output and thermal efficiency as H class gas turbines while continuing to rely on conventional air cooling of turbine blades and vanes, and time-proven materials from industrial gas turbine experience. In this paper we describe the key design features of the M701G2 gas turbine that make this possible such as the advanced 21:1 compressor with 14 stages, an advanced premix DLN combustor, etc., as well as shop load test results that were completed in 2002 at Mitsubishi’s in-house facility.

Off-Design Performance Investigation of a Low Calorific Gas Fired Two-Shaft Gas Turbine

2009 ◽  
Author(s):  
Pontus Eriksson ◽  
Magnus Genrup ◽  
Klas Jonshagen ◽  
Jens Klingmann
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Gas Generator ◽  
Dimensional Parameter ◽  
Gaseous Fuels ◽  
Surge Margin ◽  
Power Turbine ◽  
Lean Premixed ◽  
Wobbe Index ◽  
Compressor Map

Gas turbine systems are predominantly designed to be fuelled with gaseous fuels within a limited Wobbe index range (typically HHV = 45–55 MJ/Nm3 or 1200–1480 Btu/scf). When low calorific fuel gases are fired, the engine will be forced to operate outside its design envelope. The added mass flow will typically raise the cycle pressure ratio and in two-shaft designs also raise the gas generator shaft speed. Typical constraints to be considered due to the altered fuel composition are pressure loads, shaft torques, shaft overspeeds, centrifugal overloading of disks and blades, combustor flameout, surge and flutter limits for the turbomachinery. This poses limitations to usable fuel choices. In this study, the response of a natural gas fired simple cycle two-shaft gas turbine is investigated. A lean premixed combustor is also included in the model. Emphasis has been put on predicting the turbomachinery and combustor behavior as different amounts of N2 or CO2 are added to the fuel path. These two inerts are typically found in large quantities in medium and low calorific fuels. The fuels lower heating value is thus gradually changed from 50 MJ/kg (21.5 kBtu/lb) to 5MJ/kg (2.15 kBtu/lb). A model, based on the Volvo Aero Corp. VT4400 gas turbine (originally Dresser Rand DR990) characterized by one compressor and two expander maps is considered. The free turbine is operated at fixed physical speed. The operating point is plotted in the compressor map and the turbine maps at three distinct firing temperatures representing turndown from full load to bleed opening point. Gas generator speed and shaft power are shown. Surge margin and power turbine power is plotted. Overall efficiency is computed. The behavior of the Volvo lean premixed combustor is also discussed. Air split, primary zone equivalence ratio and temperature is plotted. Combustor loading, combustion intensity and pressure drop is graphed. Results are, as far as possible, given as non-dimensional parameter groups for easy comparison with other machines.

scholarly journals Developments Leading to an Axial Flow Compressor for a 25 MW Class High Efficiency Gas Turbine

1990 ◽  
Author(s):  
Y. Kashiwabara ◽  
Y. Katoh ◽  
H. Ishii ◽  
T. Hattori ◽  
Y. Matsuura ◽  
...  
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Mechanical Design ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Rotating Stall ◽  
Design Parameters ◽  
Axial Flow Compressor ◽  
Heavy Duty Gas Turbine ◽  
Flow Compressor

In this paper, the development leading to a 17-stage axial flow compressor (pressure ratio 14.7) for the 25 MW class heavy duty gas turbine H-25 is described. In the course of developing the H-25’s compressor, extensive measurements were carried out on models. Experimental results are compared with predicted values. Aerodynamic experiments covered the measurements of unsteady flows such as rotating stall and surge as well as the steady-state performance of the compressor. Based on the results of these tests, the aerodynamic and mechanical design parameters of the full scale H-25 compressor were finalized on the basis of two model compressors. Detailed measurements of the first unit of the H-25 gas turbine were carried out. Test results on the compressor are presented and show the achievement of the expected design targets.

scholarly journals A Prototype Replacement of a 100,000 Hours Operation, 25,000 KW Gas Turbine at Idemitsu Kosan Co., Ltd.

1989 ◽  
Author(s):  
R. Furukawazono ◽  
H. Ishino ◽  
T. Kamata ◽  
M. Kunihiro ◽  
M. Kubota
Keyword(s):  
Gas Turbine ◽  
Waste Heat ◽  
Pressure Ratio ◽  
Load Test ◽  
Commercial Application ◽  
Gas Temperature ◽  
Heavy Distillate ◽  
Final Shutdown ◽  
Near Future ◽  
Base Load

In September 1988, a Hitachi-GE model PG5341 gas turbine installed at the Tokuyama refinery of Idemitsu Kosan Co., Ltd. (Japan) successfully recorded 100,325 hours of base load operation over a period of 13 years with 99.4% reliability. The generated power totalled 1,341,770 MWh at the time of final shutdown. The gas turbine, burning Bunker A oil, LPG, and heavy distillate oil, had been the main equipment in a cogeneration plant with a simple heat recovery steam generator using waste heat from the exhaust gas, plus a refired boiler. It was expected that several costly hot gas path components of this turbine would have to be replaced in the near future, and it was not as fuel efficient as more modern designs, so it was decided to replace the PG5341 with a Hitachi H-25 gas turbine. This new model H-25 is designed to have a rated output of 26,200kW and an efficiency of 32.3% (LHV) at the generator terminals under ISO conditions. By the use of a pressure ratio of 14.7 (up from 10.1) and a combustor outlet gas temperature of 1,260°C (up from 980°C), it is expected that efficiency of gas turbine will be improved relatively by 18.7% on a design basis, compared with the PG5341. A factory full-load test of the prototype H-25 gas turbine was completed in August 1988 with excellent results. This machine has been in place and in operation at the Tokuyama plant since the end of November 1988. This is the first commercial application of the Hitachi H-25 advanced gas turbine.

scholarly journals FT8-55 Mechanical Drive Aeroderivative Gas Turbine: Design of Power Turbine and Full-Load Test Results

1994 ◽  
Author(s):  
E. Aschenbruck ◽  
R. Blessing ◽  
L. Turanskyj
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Material Selection ◽  
Measurement Techniques ◽  
Load Test ◽  
Civil Aviation ◽  
Test Results ◽  
Full Load ◽  
Highly Efficient ◽  
Power Turbine

A new, highly efficient 25-MW aero-derivative gas turbine, model FT8-55, has been developed for mechanical drive applications as a member of the FT8 gas turbine family which also includes two generator drive gas turbines, models FT8-30 and FT8-36, with power turbine speeds of 3000 rpm and 3600 rpm, respectively. For the new mechanical drive version FT8-55, the power turbine can be operated up to 5775 rpm at maximum continuous speed. All power turbines are equipped with gas generators, model GG8-1, which are derived from the most popular aero-engine in civil aviation, the JT8D. The first part of this paper describes design features, rotor dynamics, and material selection for the three-stage power turbine PT8-55. Rotor design permits unrestricted operation in the speed range from 2500 rpm up to maximum continuous speed. The first FT8-55 gas turbine was subjected to mechanical and performance workshop tests at different speeds and power outputs up to full-load. The second part of the paper deals with the description of the test stand arrangement for testing complete gas turbine packages as well as measurement techniques and data evaluation. Power was absorbed by a two-stage pipeline compressor, equipped with magnetic bearings and dry gas seals, which was operated in a closed loop. Thermodynamic and mechanical test results at various speeds and loads provide evidence of a highly efficient and mechanically robust gas turbine for mechanical drive applications.

Design of the 6C Heavy-Duty Gas Turbine

2003 ◽  
Author(s):  
David Harper ◽  
Devin Martin ◽  
Harold Miller ◽  
Robert Grimley ◽  
Fre´de´ric Greiner
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Load Test ◽  
Advanced Technology ◽  
General Electric ◽  
Three Stages ◽  
Flow Compressor

The MS6001C gas turbine combines the proven reliability of the General Electric gas turbine family with the advanced technology developed for the FA, FB and H machine designs. The engine configuration is a single shaft bolted rotor, driving a 50 or 60 Hz. generator though a cold end mounted load gear. Rated at 42.3 MW, with a thermal efficiency of 36.3%, the MS6001C will provide greater than a four percent increase in efficiency over the MS6001B. This paper is focused on the design and development of the MS6001C gas turbine, highlighting the commonality between this and other General Electric Power Systems (GEPS) and General Electric Aircraft Engines (GEAE) designs, as well as introducing some new and innovative features. The new high efficiency, 12 stage, axial flow compressor, features a 19:1 pressure ratio with three stages of variable guide vanes. The can annular, six chamber, Dry Low NOx (DLN-2.5H) combustion system is scaled from field proven, low emission technology. The turbine incorporates three stages, two cooled blade rows, and operates at a 1327°C firing temperature. After a thorough factory full speed no load test has been conducted, the first MS6001C engine will be shipped to a customer site in Kemalpasalzmir Turkey, where an instrumented full load test will be conducted to validate the design.

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