Parametric Analysis of Existing Gas Turbines With Inlet Evaporative and Overspray Fogging

2005 ◽  
Vol 127 (1) ◽  
pp. 145-158 ◽  
Author(s):  
R. Bhargava ◽  
C. B. Meher-Homji
Keyword(s):  
Gas Turbine ◽  
Performance Improvement ◽  
Gas Turbines ◽  
Parametric Analysis ◽  
Design Parameters ◽  
Performance Parameters ◽  
Heavy Duty ◽  
Wide Range ◽  
The World ◽  
Turbine Design

With deregulation in the power generation market and a need for flexibility in terms of power augmentation during the periods of high electricity demand, power plant operators all over the world are exploring means to augment power from both the existing and new gas turbines. An approach becoming increasingly popular is that of the high pressure inlet fogging. In this paper, the results of a comprehensive parametric analysis on the effects of inlet fogging on a wide range of existing gas turbines are presented. Both evaporative and overspray fogging conditions have been analyzed. The results show that the performance parameters indicative of inlet fogging effects have a definitive correlation with the key gas turbine design parameters. In addition, this study indicates that the aeroderivative gas turbines, in comparison to the heavy-duty industrial machines, have higher performance improvement due to inlet fogging effects. Plausible reasons for the observed trends are discussed. This paper represents the first systematic study on the effects of inlet fogging for a large number (a total of 67) of gas turbines available from the major gas turbine manufacturers.

Parametric Analysis of Existing Gas Turbines With Inlet Evaporative and Overspray Fogging

2002 ◽  
Author(s):  
R. Bhargava ◽  
C. B. Meher-Homji
Keyword(s):  
Gas Turbine ◽  
Performance Improvement ◽  
Gas Turbines ◽  
Parametric Analysis ◽  
Design Parameters ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Performance Parameters ◽  
Wide Range ◽  
Turbine Design

With deregulation in the power generation market and the need for flexibility in terms of power augmentation during periods of high electricity demand, power plant operators all over the world are exploring means to augment power from both existing and new gas turbines. An approach becoming increasingly popular is that of high pressure fogging. In this paper, the results of a comprehensive parametric analysis on the effects of inlet fogging on a wide range of existing gas turbines have been presented. Both evaporative and overspray fogging conditions have been analyzed. The results of this study show that the performance parameters indicative of inlet fogging effects have definitive correlation with the key gas turbine design parameters. In addition, this study indicates that aeroderivative gas turbines, in comparison to the industrial machines, have higher performance improvement due to the inlet fogging effects. Plausible reasons for the observed trends are discussed in this paper. This paper represents the first systematic study on the effects of inlet fogging for a large number (a total of 67) of gas turbine engines available from major gas turbine manufacturers.

Design Parameters Prediction of New Type Gas Turbine Based on a Hybrid GRA-SVM Prediction Model

2017 ◽  
Author(s):  
Tingting Wei ◽  
Dengji Zhou ◽  
Jinwei Chen ◽  
Yaoxin Cui ◽  
Huisheng Zhang
Keyword(s):  
Prediction Model ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Technology Development ◽  
Design Parameters ◽  
Support Vector ◽  
Performance Parameters ◽  
New Type ◽  
Equipment Manufacture ◽  
Grey Relational

Since the late 1930s, gas turbine has begun to develop rapidly. To improve the economic and safety of gas turbine, new types were generated frequently by Original Equipment Manufacture (OEM). In this paper, a hybrid GRA-SVM prediction model is established to predict the main design parameters of new type gas turbines, based on the combination of Grey Relational Analysis (GRA) and Support Vector Machine (SVM). The parameters are classified into two types, system performance parameters reflecting market demands and technology development, and component performance parameters reflecting technology development and coupling connections. The regularity based on GRA determines the prediction order, then new type gas turbine parameters can be predicted with known system parameters. The model is verified by the application to SGT600. In this way, the evolution rule can be obtained with the development of gas turbine technology, and the improvement potential of several components can be predicted which will provide supports for overall performance design.

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.

A Comparative Analysis of Single Nozzle and Multiple Nozzles Arrangements for Syngas Combustion in Heavy Duty Gas Turbine

2016 ◽  
Vol 139 (2) ◽  
Author(s):  
Shi Liu ◽  
Hong Yin ◽  
Yan Xiong ◽  
Xiaoqing Xiao
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Combined Cycle ◽  
Heavy Duty ◽  
Gas Turbine Combustor ◽  
Integrated Gasification Combined Cycle ◽  
Wide Range ◽  
Heavy Duty Gas Turbine ◽  
Integrated Gasification

Heavy duty gas turbines are the core components in the integrated gasification combined cycle (IGCC) system. Different from the conventional fuel for gas turbine such as natural gas and light diesel, the combustible component acquired from the IGCC system is hydrogen-rich syngas fuel. It is important to modify the original gas turbine combustor or redesign a new combustor for syngas application since the fuel properties are featured with the wide range hydrogen and carbon monoxide mixture. First, one heavy duty gas turbine combustor which adopts natural gas and light diesel was selected as the original type. The redesign work mainly focused on the combustor head and nozzle arrangements. This paper investigated two feasible combustor arrangements for the syngas utilization including single nozzle and multiple nozzles. Numerical simulations are conducted to compare the flow field, temperature field, composition distributions, and overall performance of the two schemes. The obtained results show that the flow structure of the multiple nozzles scheme is better and the temperature distribution inside the combustor is more uniform, and the total pressure recovery is higher than the single nozzle scheme. Through the full scale test rig verification, the combustor redesign with multiple nozzles scheme is acceptable under middle and high pressure combustion test conditions. Besides, the numerical computations generally match with the experimental results.

scholarly journals Review of Design Parameters in Gas Turbines for the Prospective User

1988 ◽  
Author(s):  
Robert E. Dundas
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Compressor Blade ◽  
Design Parameters ◽  
Temperature Profiles ◽  
Case Histories ◽  
Compressor Performance ◽  
Turbine Design ◽  
Industry Experience ◽  
Prospective User

This paper is based on five selected areas of gas turbine design that should be reviewed by prospective purchasers of gas turbines in the specification and procurement phase, in view of adverse industry experience associated with them. The details that should be requested and reviewed, and the criteria that should be met, are discussed. Case histories of adverse industry experience are provided for substantiation of the recommendations. The design areas discussed are: 1. Compressor-blade resonance diagrams 2. Compressor performance maps 3. Turbine-blade resonance diagrams 4. Temperature profiles in turbine flowpath 5. Response to combustor flameout

Gas Turbine Operating in Combined and Regenerative Cycles Using Liquid Metal Heat Exchangers

1993 ◽  
Author(s):  
M. A. Perkavec
Keyword(s):  
Heat Exchange ◽  
Liquid Metal ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Nuclear Power ◽  
High Heat ◽  
Combined Cycle ◽  
Design Parameters ◽  
Wide Range ◽  
Regenerative Cycle

Liquid metal technology for heat transfer was developed for use in nuclear power stations. Applied to a gas turbine regenerative cycle plant, it makes high heat exchange rates in the regenerator, and low pressure losses as well on the air side as on the exhaust side economically possible. Its application permits combined cycle as well as regenerative cycle operation of the same gas turbine. Mixed operation in any ratio is also easily accomplished, so that the ratio of heat and electricity produced by the gas turbine plant is variable within a wide range. This paper presents the results of thermodynamic calculations for such plants and describes the optimization of design parameters. Influences of the individual parameters of the regenerative cycle on the power output and efficiency of the plant are examined, and the reasonable limits for this application are outlined. The advantages of applying liquid metal technology to gas turbines, such as a virtually pressureless liquid metal system, flexible operation, and separate optimization of the heat exchange coefficients for the air and exhaust flows are discussed. Reference is also made to emissions, which are more complicated than those for combined or regenerative cycles because the plant is operated in both modes.

scholarly journals Thermal calculations and NOx emission analysis of a micro gas turbine system without a recuperator

2021 ◽  
pp. 336-336
Author(s):  
Yunyun Wang ◽  
Jiang Liu ◽  
Luyu Wang ◽  
Fu Zaiguo ◽  
Peifen Weng
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Nox Emission ◽  
Design Parameters ◽  
Thermal Calculation ◽  
Performance Parameters ◽  
Micro Gas Turbine ◽  
Thermal Calculations

A thermal calculation based on a table of thermal properties of gas was carried out for a micro gas turbine system without a recuperator. The performance parameters of the micro gas turbine system were obtained. The results of the thermal calculations were verified using Aspen Plus, and it shows that the thermal calculations fit well with the Aspen simulation results. Based on this thermal calculation method, the variation of the performance parameters of the micro gas turbine system under different pressure and temperature ratios was analyzed. The results show that there is no optimum pressure ratio within the general design parameters of micro gas turbines, which leads to extreme values of thermal efficiency. The NOx generation in the combustion chamber of the micro gas turbine based on the Zeldovich mechanism was modeled and analyzed by coupling the one-dimensional thermal calculation model with the NOx emission model. The relationship between NOx generation rate, molar fuel factor, the characteristic pressure, and the characteristic temperature was obtained. The results of the analysis show that, in terms of controlling NOx emissions from a gas turbine, the use of an increased pressure ratio has a significant advantage over an increased temperature ratio to improve the thermal efficiency of the micro gas turbine.

Fuel Flexibility With Low Emissions in Heavy Duty Industrial Gas Turbines

2010 ◽  
Author(s):  
Predrag Popovic ◽  
Geoffrey Myers ◽  
Joseph Citeno ◽  
Richard Symonds ◽  
Anthony Campbell
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Premixed Combustion ◽  
Heavy Duty ◽  
Gaseous Fuels ◽  
Fuel Flexibility ◽  
Wide Range ◽  
Industrial Gas Turbines ◽  
Combustion Technology ◽  
Industrial Gas Turbine

In the 1990’s GE introduced low-emissions combustion technology primarily for gas turbines burning natural gas (NG) fuel. Today, industrial gas turbine fuels are more diverse than ever. As a result, diverse diffusion and premixed combustion technologies are used to burn gaseous fuels with low emissions. This paper summarizes combustion and gas turbine control challenges when firing diverse fuels, and advancements in technology when burning a wide range of fuels with low emissions.

scholarly journals Feasibility of a Helium Closed-Cycle Gas Turbine for UAV Propulsion

2020 ◽  
Vol 11 (1) ◽  
pp. 28
Author(s):  
Emmanuel O. Osigwe ◽  
Arnold Gad-Briggs ◽  
Theoklis Nikolaidis
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Low Noise ◽  
Closed Cycle ◽  
Propulsion Systems ◽  
Component Design ◽  
Readiness Level ◽  
Aerial Vehicle ◽  
Turbine Design

When selecting a design for an unmanned aerial vehicle, the choice of the propulsion system is vital in terms of mission requirements, sustainability, usability, noise, controllability, reliability and technology readiness level (TRL). This study analyses the various propulsion systems used in unmanned aerial vehicles (UAVs), paying particular focus on the closed-cycle propulsion systems. The study also investigates the feasibility of using helium closed-cycle gas turbines for UAV propulsion, highlighting the merits and demerits of helium closed-cycle gas turbines. Some of the advantages mentioned include high payload, low noise and high altitude mission ability; while the major drawbacks include a heat sink, nuclear hazard radiation and the shield weight. A preliminary assessment of the cycle showed that a pressure ratio of 4, turbine entry temperature (TET) of 800 °C and mass flow of 50 kg/s could be used to achieve a lightweight helium closed-cycle gas turbine design for UAV mission considering component design constraints.

Design, Development and Application of Vehicle Gas Turbine Engines

1966 ◽  
Vol 181 (1) ◽  
pp. 149-172
Author(s):  
P. A. Phillips ◽  
Peter Spear
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Low Cost ◽  
Engine Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Development ◽  
Turbine Engine ◽  
Wide Range ◽  
Cycle Temperature

After briefly summarizing worldwide automotive gas turbine activity, the paper analyses the power plant requirements of a wide range of vehicle applications in order to formulate the design criteria for acceptable vehicle gas turbines. Ample data are available on the thermodynamic merits of various gas turbine cycles; however, the low cost of its piston engine competitor tends to eliminate all but the simplest cycles from vehicle gas turbine considerations. In order to improve the part load fuel economy, some complexity is inevitable, but this is limited to the addition of a glass ceramic regenerator in the 150 b.h.p. engine which is described in some detail. The alternative further complications necessary to achieve satisfactory vehicle response at various power/weight ratios are examined. Further improvement in engine performance will come by increasing the maximum cycle temperature. This can be achieved at lower cost by the extension of the use of ceramics. The paper is intended to stimulate the design application of the gas turbine engine.

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