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.

Strength Design and Reliability Evaluation of a Hybrid Ceramic Stator Vane for Industrial Gas Turbines

1995 ◽  
Vol 117 (2) ◽  
pp. 245-250 ◽  
Author(s):  
K. Nakakado ◽  
T. Machida ◽  
H. Miyata ◽  
T. Hisamatsu ◽  
N. Mori ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Power Plants ◽  
Metal Structure ◽  
Reliability Evaluation ◽  
Combustion Gas ◽  
Strength Design ◽  
Stator Vane ◽  
Industrial Gas Turbines ◽  
Hybrid Ceramic

Employing ceramic materials for the critical components of industrial gas turbines is anticipated to improve the thermal efficiency of power plants. We developed a first-stage stator vane for a 1300°C class, 20-MW industrial gas turbine. This stator vane has a hybrid ceramic/metal structure, to increase the strength reliability of brittle ceramic parts, and to reduce the amount of cooling air needed for metal parts as well. The strength design results of a ceramic main part are described. Strength reliability evaluation results are also provided based on a cascade test using combustion gas under actual gas turbine running conditions.

CTV: A New Method for Mapping a Full Scale Prototype of an Axial Compressor

1996 ◽  
Author(s):  
Vasco Mezzedimi ◽  
Pierluigi Nava ◽  
Dave Hamilla
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Theoretical Basis ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Test Vehicle ◽  
Testing Method ◽  
Area Reduction ◽  
Speed Range ◽  
Compressor Inlet

The full mapping of a new gas turbine axial compressor at different speeds, IGV settings and pressure ratios (from choking to surge) has been performed utilizing a complete gas turbine with a suitable set of modifications. The main additions and modifications, necessary to transform the turbine into the Compressor Test Vehicle (CTV), are: - Compressor inlet throttling valve addition - Compressor discharge bleed valve addition - Turbine 1st stage nozzle area reduction - Starting engine change (increase in output and speed range). This method has been successfully employed on two different single shaft heavy-duty gas turbines (with a power rating of 11MW and 170 MW respectively). The paper describes the theoretical basis of this testing method and a specific application with the above mentioned 170 MW machine.

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.

Performance Evaluation of Selected Combustion Gas Turbine Cogeneration Systems Based on First and Second-Law Analysis

1990 ◽  
Vol 112 (1) ◽  
pp. 117-121 ◽  
Author(s):  
F. F. Huang
Keyword(s):  
Performance Evaluation ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Decision Makers ◽  
Utilization Efficiency ◽  
Second Law ◽  
Pinch Point ◽  
Combustion Gas ◽  
Second Law Analysis ◽  
Industrial Gas Turbines

The thermodynamic performance of selected combustion gas turbine cogeneration systems has been studied based on first-law as well as second-law analysis. The effects of the pinch point used in the design of the heat recovery steam generator, and pressure of process steam on fuel-utilization efficiency (first-law efficiency), power-to-heat ratio, and second-law efficiency, are examined. Results for three systems using state-of-the-art industrial gas turbines show clearly that performance evaluation based on first-law efficiency alone is inadequate. Decision makers should find the methodology contained in this paper useful in the comparison and selection of cogeneration systems.

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.

scholarly journals Design and Test of a New Axial Compressor for the Nuovo Pignone Heavy Duty Gas Turbines

1996 ◽  
Author(s):  
Erio Benvenuti
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Dynamic Pressure ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Leading Edge ◽  
Meridional Flow ◽  
Heavy Duty ◽  
Pressure Transducers ◽  
Easy Integration

This axial compressor design was primarily focused to increase the power rating of the current Nuovo Pignone PGT10 Heavy-Duty gas turbine by 10%. In addition, the new 11-stage design favourably compares with the existing 17-stage compressor in terms of simplicity and cost. By seating the flowpath and blade geometry, the new aerodynamic design can be applied to gas turbines with different power ratings as well. The reduction in the stage number was achieved primarily through the meridional flow-path redesign. The resulting higher blade peripheral speeds achieve larger stage pressure ratios without increasing the aerodynamic loadings. Wide chord blades keep the overall length unchanged thus assuring easy integration with other existing components. The compressor performance map was extensively checked over the speed range required for two-shaft gas turbines. The prototype unit was installed on a special PGT10 gas turbine setup, that permitted the control of pressure ratio independently from the turbine matching requirements. The flowpath instrumentation included strain-gages, dynamic pressure transducers and stator vane leading edge aerodynamic probes to determine individual stage characteristics. The general blading vibratory behavior was proved fully satisfactory. With minor adjustments to the variable stator settings the front stage aerodynamic matching was optimized and the design performance was achieved.

Axial Compressor Degradation Effects on Heavy Duty Gas Turbines Overall Performances

2013 ◽  
Author(s):  
Pio Astrua ◽  
Stefano Cecchi ◽  
Stefano Piola ◽  
Andrea Silingardi ◽  
Federico Bonzani
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Axial Compressor ◽  
Performance Parameters ◽  
Heavy Duty ◽  
Compressor Blades ◽  
Modular Model ◽  
Secondary Air ◽  
The Impact ◽  
Insight Into

The operation of a gas turbine is the result of the aero-thermodynamic matching of several components which necessarily experience aging and degradation over time. An approach to treat degradation phenomena of the axial compressor is provided, with an insight into the impact they have on compressor operation and on overall GT performances. The analysis is focused on the surface fouling of compressor blades and on rotor tip clearances variation. A modular model is used to simulate the gas turbine operation in design and off-design conditions and the aerodynamic impact of fouling and rotor tip clearances increase is assessed by means of dedicated loss and deviation correlations implemented in the 1D mid-streamline code of the compressor modules. The two different degradation sources are individually considered and besides the overall GT performance parameters, the analysis includes an evaluation of the compressor degradation impact on the secondary air system.

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.

An analytical approach to predicting particle deposit by fouling in the axial compressor of the industrial gas turbine

2005 ◽  
Vol 219 (3) ◽  
pp. 203-212 ◽  
Author(s):  
T W Song ◽  
J L Sohn ◽  
T S Kim ◽  
J H Kim ◽  
S T Ro
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Particle Deposition ◽  
Axial Compressor ◽  
Design Parameters ◽  
Compressor Blades ◽  
Particle Distributions ◽  
Industrial Gas Turbines ◽  
Industrial Gas Turbine ◽  
Physical Phenomena

The gas turbine performance deteriorates with increased operating hours. Fouling in the axial compressor is an important factor for the performance degradation of gas turbines. Airborne particles entering the compressor with the air adhere to the blade surface and result in the change of the blade shape, which directly influences the compressor performance. It is difficult to exactly understand the mechanism of compressor fouling because of its slow growth and different length scales of compressor blades. In this study, an analytical method to predict the particle motion in the axial compressor and the characteristics of particle deposition onto blade is proposed as an approach to investigating physical phenomena of fouling in the axial compressor of industrial gas turbines. Calculated results using the proposed method and comparison with measured data demonstrate the feasibility of the model. It was also found that design parameters of the axial compressor such as chord length, solidity, and number of stages are closely related to the fouling phenomena. Likewise, the particle size and patterns of particle distributions are also important factors related to fouling phenomena in the axial compressor.

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.

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