Compressor Discharge Brush Seal for Gas Turbine Model 7EA

2001 ◽  
Author(s):  
Steve Ingistov
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Unit ◽  
Labyrinth Seal ◽  
Compressed Air ◽  
Air Leakage ◽  
Heavy Duty ◽  
Gas Turbine Unit ◽  
Brush Seal ◽  
Industrial Gas Turbines

Single shaft-heavy-duty- industrial gas turbines are extremely sensitive to compressed air bypassing at compressor discharge plane. This plane represents the highest pressure location in entire Gas Turbine Unit (GTU). Standard method to minimize compressed air leakage is labyrinth seal that is integral part of the cylindrical element here called “inner barrel”. The “inner barrel” is also the part of compressor discharge diffuser. This Paper describes the efforts related to conversion of standard labyrinth seal into the hybrid seal that is combination of labyrinth and brush seals.

Compressor Discharge Brush Seal for Gas Turbine Model 7EA

2002 ◽  
Vol 124 (2) ◽  
pp. 301-305 ◽  
Author(s):  
Steve Ingistov
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Unit ◽  
Labyrinth Seal ◽  
Compressed Air ◽  
Air Leakage ◽  
Heavy Duty ◽  
Gas Turbine Unit ◽  
Brush Seal ◽  
Industrial Gas Turbines

Single-shaft, heavy-duty industrial gas turbines are extremely sensitive to compressed air bypassing at compressor discharge plane. This plane represents the highest pressure location in entire gas turbine unit (GTU). Standard method to minimize compressed air leakage is labyrinth seal that is integral part of the cylindrical element here called “inner barrel.” The inner barrel is also the part of compressor discharge diffuser. This paper describes the efforts related to conversion of standard labyrinth seal into the hybrid seal that is combination of labyrinth and brush seals.

scholarly journals Review of Recuperator used in Micro Gas Turbine

2021 ◽  
Vol 9 (VIII) ◽  
pp. 634-637
Author(s):  
Yastuti Rao Gautam
Keyword(s):  
Heat Transfer ◽  
Pressure Drop ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Unit ◽  
High Reliability ◽  
Compressed Air ◽  
Exhaust Gas ◽  
Gas Turbine Unit ◽  
Micro Gas Turbine

Micro gas turbines are an auspicious technology for power generation because of their small size, low pollution, low maintenance, high reliability and natural fuel used. Recuperator is vital requirement in micro gas turbine unit for improve the efficiency of micro turbine unit . Heat transfer and pressure drop characteristics are important for designing an efficient recuperator. Recuperators preheat compressed air by transfer heat from exhaust gas of turbines, thus reducing fuel consumption and improving the thermal efficiency of micro gas turbine unit from 16–20% to 30%. The fundamental principles for optimization design of PSR are light weight, low pressure loss and high heat-transfer between exhaust gas to compressed air. There is many type of recuperator used in micro gas turbine like Annular CWPS recuperator , recuperator with involute-profile element , honey well , swiss-Roll etc . In this review paper is doing study of Heat transfer and pressure drop characteristics of many types recuperator.

scholarly journals Impact of compressed air energy storage demands on gas turbine performance

2020 ◽  
pp. 095765092090627 ◽  
Author(s):  
Uyioghosa Igie ◽  
Marco Abbondanza ◽  
Artur Szymański ◽  
Theoklis Nikolaidis
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Engine Performance ◽  
Compressed Air ◽  
Design Stage ◽  
Simulation Code ◽  
Ratio Distribution ◽  
Stall Margin ◽  
Industrial Gas Turbines

Industrial gas turbines are now required to operate more flexibly as a result of incentives and priorities given to renewable forms of energy. This study considers the extraction of compressed air from the gas turbine; it is implemented to store heat energy at periods of a surplus power supply and the reinjection at peak demand. Using an in-house engine performance simulation code, extractions and injections are investigated for a range of flows and for varied rear stage bleeding locations. Inter-stage bleeding is seen to unload the stage of extraction towards choke, while loading the subsequent stages, pushing them towards stall. Extracting after the last stage is shown to be appropriate for a wider range of flows: up to 15% of the compressor inlet flow. Injecting in this location at high flows pushes the closest stage towards stall. The same effect is observed in all the stages but to a lesser magnitude. Up to 17.5% injection seems allowable before compressor stalls; however, a more conservative estimate is expected with higher fidelity models. The study also shows an increase in performance with a rise in flow injection. Varying the design stage pressure ratio distribution brought about an improvement in the stall margin utilized, only for high extraction.

scholarly journals Maintenance of Industrial Gas Turbines

1975 ◽  
Author(s):  
R. H. Knorr ◽  
G. Jarvis
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Heavy Duty ◽  
Factors Affecting ◽  
Maintenance Program ◽  
Industrial Gas Turbines ◽  
Heavy Duty Gas Turbine ◽  
Maintenance Requirements

This paper describes the maintenance requirements of the heavy-duty gas turbine. The various inspections and factors affecting maintenance are defined, and basic guidelines are presented for a planned maintenance program.

Dry, Low Emissions for the ‘H’ Heavy-Duty Industrial Gas Turbines: Full-Scale Combustion System Rig Test Results

2003 ◽  
Author(s):  
Geoff Myers ◽  
Dan Tegel ◽  
Markus Feigl ◽  
Fred Setzer ◽  
William Bechtel ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Full Scale ◽  
Combustion System ◽  
Heavy Duty ◽  
Test Program ◽  
Industrial Gas Turbines ◽  
Inlet Conditions

The lean, premixed DLN2.5H combustion system was designed to deliver low NOx emissions from 50% to 100% load in both the Frame 7H (60 Hz) and Frame 9H (50 Hz) heavy-duty industrial gas turbines. The H machines employ steam cooling in the gas turbine, a 23:1 pressure ratio, and are fired at 1440 C (2600 F) to deliver over-all thermal efficiency for the combined-cycle system near 60%. The DLN2.5H combustor is a modular can-type design, with 14 identical chambers used on the 9H machine, and 12 used on the smaller 7H. On a 9H combined-cycle power plant, both the gas turbine and steam turbine are fired using the 14-chamber DLN2.5H combustion system. An extensive full-scale, full-pressure rig test program developed the fuel-staged dry, low emissions combustion system over a period of more than five years. Rig testing required test stand inlet conditions of over 50 kg/s at 500 C and 28 bar, while firing at up to 1440 C, to simulate combustor operation at base load. The combustion test rig simulated gas path geometry from the discharge of the annular tri-passage diffuser through the can-type combustion liner and transition piece, to the inlet of the first stage turbine nozzle. The present paper describes the combustion system, and reports emissions performance and operability results over the gas turbine load and ambient temperature operating range, as measured during the rig test program.

Degradation of Compressor Blades of Gas Turbines in Coastal and Industrial Environment

2016 ◽  
Vol 1133 ◽  
pp. 371-375 ◽  
Author(s):  
Salmi Mohd Yunus ◽  
Saiful Adilin Sekari ◽  
Mohd Hafiz Abdul Ghaffar
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Unit ◽  
Oil Refinery ◽  
Oil Refining ◽  
Degradation Mechanisms ◽  
Gas Turbine Unit ◽  
Compressor Blades ◽  
Industrial Environment ◽  
Gas Turbine Compressor

Gas turbine compressor blades will age and degrade in their operation. There are a lot of factors that will contribute to the degradation mechanisms and its acceleration. These factors encompass the site location, the site conditions including the aspect of air quality, water washing practice, etc. A study undertaken by Materials Engineering Group of TNB Research Sdn Bhd on 2 units of gas turbine compressor those are located near to the sea around Peninsular of Malaysia, to determine the degradation mechanisms of the blades. All these gas turbine units are located in different industrial environment. The first gas turbine unit, so called GTA is located in coastal, petrochemicals production and crude oil refining environment. The second gas turbine unit, so called GTB, located in coastal and industrial environment. The surrounding industries of GTB including oil refinery, chemical, ship fabrication and etc. This paper reports the degradation type of those gas turbine units’ compressor blades with their contributing factors.

scholarly journals Technical and economic assessment of the parameters of thermal schemes of thermal power plants with a hydrogen generator

2021 ◽  
Vol 23 (2) ◽  
pp. 84-92
Author(s):  
G. E. Marin ◽  
B. M. Osipov ◽  
A. R. Akhmetshin
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Power Plants ◽  
Turbine Unit ◽  
Thermal Power ◽  
Component Composition ◽  
Automated System ◽  
Gas Turbine Unit ◽  
Turbine Plant ◽  
Gas Turbine Plant

THE PURPOSE. The study is aimed at studying the effect of fuel gases of various component composition on the environmental performance of the GE 6FA gas turbine unit. Consider using hydrogen as primary sweat to minimize emissions and improve performance of the GE 6FA gas turbine. METHODS. To achieve this goal, the ASGRET (Automated system for gas-dynamic calculations of power turbomachines) software package was used. RESULTS. The article discusses promising directions for the utilization of CO2 using highly efficient technologies with further use or disposal. A mathematical model of a GE 6FA gas turbine unit, diagrams of changes in the main characteristics and the composition of emissions when operating on various types of fuel, including hydrogen, are presented. CONCLUSION. The studies carried out show that a change in the component composition of the gas affects the energy characteristics of the engine. The method for determining the quantitative composition of COx, NOx, SOx in the exhaust gases of a gas turbine plant is presented. The transition to the reserve fuel kerosene leads to an increase in the amount of emissions, which must be taken into account when designing systems for capturing harmful emissions with a dual-fuel fuel gas supply system. The use of hydrogen as a fuel for gas turbines allows to reduce not only the cost of fuel preparation, but also to minimize emissions and improve the performance of the gas turbine plant.

Operating Experience in Refinery Application of the 13MW-Class Heavy Duty MF-111 Gas Turbine Engine

1990 ◽  
Author(s):  
J. Masada ◽  
I. Fukue
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Operating Experience ◽  
Combined Cycle ◽  
Outlet Temperature ◽  
Heavy Duty ◽  
Turbine Engine ◽  
Industrial Gas Turbines ◽  
Heavy Duty Gas Turbine ◽  
Temperature Levels

A new, 13MW class, heavy duty gas turbine, the “MF-111” was developed for use as a prime mover for cogeneration, combined cycle and repowering applications. The use of such equipment in refineries presents special challenges as regards the combustion of nonstandard fuels, tolerance of industrial environments, and accomodation of site-specific design requirements. Such circumstances add substantially to the tasks of proving and adjusting the design of a new gas turbine, meeting stringent emissions requirements and introducing to the world of industrial gas turbines the benefits of F-class (1250°C burner outlet temperature) levels of thermodynamic performance. This paper describes how these challenges have successfully been met during the three calendar years and ten machine-years of MF-111 refinery-application experience accumulated to-late.

scholarly journals Design Analysis of Micro Gas Turbines in Closed Cycles

Energies ◽  
2020 ◽  
Vol 13 (21) ◽  
pp. 5790
Author(s):  
Krzysztof Kosowski ◽  
Marian Piwowarski
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Gas Turbines ◽  
Turbine Unit ◽  
High Efficiency ◽  
Volume Flow Rate ◽  
Gas Turbine Unit ◽  
Compressor Inlet ◽  
Similar Range ◽  
Working Media

The problems faced by designers of micro-turbines are connected with a very small volume flow rate of working media which leads to small blade heights and a high rotor speed. In the case of gas turbines this limitation can be overcome by the application of a closed cycle with very low pressure at the compressor inlet (lower than atmospheric pressure). In this way we may apply a micro gas turbine unit of accepted efficiency to work in a similar range of temperatures and the same pressure ratios, but in the range of smaller pressure values and smaller mass flow rate. Thus, we can obtain a gas turbine of a very small output but of the efficiency typical of gas turbines with a much higher power. In this paper, the results of the thermodynamic calculations of the turbine cycles are discussed and the designed gas turbine flow parts are presented. Suggestions of the design solutions of micro gas turbines for different values of power output are proposed. This new approach to gas turbine arrangement makes it possible to build a gas turbine unit of a very small output and a high efficiency. The calculations of cycle and gas turbine design were performed for different cycle parameters and different working media (air, nitrogen, hydrogen, helium, xenon and carbon dioxide).

Flexible Spacers Compressor Stator Blades for Heavy Industrial Gas Turbines Model 7EA

2003 ◽  
Author(s):  
Steve Ingistov
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Field Experience ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Combustion Gas ◽  
Mechanical Integrity ◽  
Industrial Gas Turbines ◽  
Last Stage

This paper describes efforts to upgrade the mechanical integrity of axial compressor stator blades. The blades under discussion are part of an axial compressor of a heavy duty industrial Combustion Gas Turbine (CGT) made by GE, frame No. 7, model EA. The axial compressor stator blades, in the later stages of compression, are kept in required position by spacers or shims shaped to match the root profile of the blades. These spacers/shims may be as thick as 1/4 of an inch and as thin as 1/32 of an inch. These spacers/shims tend to wiggle out of the slots and eventually liberate themselves from the stator. This paper introduces a proposed solution to minimize liberation of the spacer/shims by introduction of flexible spacers/shims. This paper also describes field experience with loss of the stator blades in the last stage of compression, due to aerodynamic disturbances.

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