scholarly journals Thermoeconomic Analysis of Gas Turbine Based Cycles

1999 ◽  
Author(s):  
A. F. Massardo ◽  
M. Scialò
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Modular Structure ◽  
Simple Cycle ◽  
Inlet Temperature ◽  
Specific Work ◽  
Fuel Cost ◽  
Turbine Inlet Temperature ◽  
Efficiency Cost ◽  
The Cost

The thermoeconomic analysis of gas turbine based cycles is presented and discussed in this paper. The thermoeconomic analysis has been performed using the ThermoEconomic Modular Program (TEMP V.5.0) developed by the Authors (Agazzani and Massardo, 1997). The modular structure of the code allows the thermoeconomic analysis for different scenarios (turbine inlet temperature, pressure ratio, fuel cost, installation costs, operating hours per year, etc.) of a large number of advanced gas turbine cycles to be obtained in a fast and reliable way. The simple cycle configuration results have been used to assess the cost functions and coefficient values. The results obtained for advanced gas turbine based cycles (intercooled, re-heated, regenerated and their combinations) are presented using new and useful representations: cost vs. efficiency, cost vs. specific work, and cost vs. pressure ratio. The results, including productive diagram configurations, are discussed in detail and compared to one another.

Thermoeconomic Analysis of Gas Turbine Based Cycles

2000 ◽  
Vol 122 (4) ◽  
pp. 664-671 ◽  
Author(s):  
A. F. Massardo ◽  
M. Scialo`
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Modular Structure ◽  
Simple Cycle ◽  
Inlet Temperature ◽  
Specific Work ◽  
Fuel Cost ◽  
Turbine Inlet Temperature ◽  
Efficiency Cost ◽  
The Cost

The thermoeconomic analysis of gas turbine based cycles is presented and discussed in this paper. The thermoeconomic analysis has been performed using the ThermoEconomic Modular Program (TEMP V.5.0) developed by Agazzani and Massardo (1997). The modular structure of the code allows the thermoeconomic analysis for different scenarios (turbine inlet temperature, pressure ratio, fuel cost, installation costs, operating hours per year, etc.) of a large number of advanced gas turbine cycles to be obtained in a fast and reliable way. The simple cycle configuration results have been used to assess the cost functions and coefficient values. The results obtained for advanced gas turbine based cycles (inter-cooled, re-heated, regenerated and their combinations) are presented using new and useful representations: cost versus efficiency, cost versus specific work, and cost versus pressure ratio. The results, including productive diagram configurations, are discussed in detail and compared to one another. [S0742-4795(00)01903-7]

A Parametric Analysis for Optimal Selection of a Gas Turbine Cogeneration System

2004 ◽  
Author(s):  
K. Sarabchi ◽  
A. Ansari
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Computer Code ◽  
Primary Energy ◽  
Inlet Temperature ◽  
Fuel Cost ◽  
Energy Usage ◽  
Turbine Inlet Temperature ◽  
Cogeneration System ◽  
Selection Of

Cogeneration is a simultaneous production of heat and electricity in a single plant using the same primary energy. Usage of a cogeneration system leads to fuel energy saving as well as air pollution reduction. A gas turbine cogeneration plant (GTCP) has found many applications in industries and institutions. Although fuel cost is usually reduced in a cogeneration system but the selection of a system for a given site optimally involves detailed thermodynamic and economical investigations. In this paper the performance of a GTCP was investigated and an approach was developed to determine the optimum size of the plant to meet the electricity and heat demands of a given site. A computer code, based on this approach, was developed and it can also be used to examine the effect of key parameters like pressure ratio, turbine inlet temperature, utilization period, and fuel cost on the economics of GTCP.

scholarly journals 100s and 1000s Mw Open and Semi-Closed Cycle Gas Turbines for Base and Peak Operation

1974 ◽  
Author(s):  
V. V. Uvarov ◽  
V. S. Beknev ◽  
E. A. Manushin
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Simple Cycle ◽  
Inlet Temperature ◽  
Closed Cycle ◽  
Turbine Inlet Temperature ◽  
Unit Capacity ◽  
Temperature And Pressure ◽  
Different Levels

There are two different approaches to develop the gas turbines for power. One can get some megawatts by simple cycle or by more complex cycle units. Both units require very different levels of turbine inlet temperature and pressure ratio for the same unit capacity. Both approaches are discussed. These two approaches lead to different size and efficiencies of gas turbine units for power. Some features of the designing problems of such units are discussed.

scholarly journals Gas Turbine and Combined Cycle Technologies for Power and Efficiency Enhancement in Power Plants

1994 ◽  
Author(s):  
Meherwan P. Boyce ◽  
Cyrus B. Meher-Homji ◽  
A. N. Lakshminarasimha
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Specific Work ◽  
Efficiency Enhancement ◽  
Turbine Inlet Temperature ◽  
Cycle Efficiency ◽  
Original Equipment Manufacturers

A wide variety of gas turbine based cycles exist in the market today with several technologies being promoted by individual Original Equipment Manufacturers. This paper is focused on providing users with a conceptual framework within which to view these cycles and choose suitable options for their needs. A basic parametric analysis is provided to show the interdependency of Turbine Inlet Temperature (TIT) and Pressure Ratio on cycle efficiency and specific work.

The influences of turbine blade mean temperature and component efficiencies on coolant optimization in the gas turbine

1997 ◽  
Vol 211 (2) ◽  
pp. 181-190 ◽  
Author(s):  
B W Martin ◽  
A Brown ◽  
M Finnis
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Inlet Temperature ◽  
Specific Work ◽  
Optimum Conditions ◽  
Gas Generator ◽  
Turbine Inlet Temperature ◽  
Engine Efficiency ◽  
Compressor Pressure Ratio ◽  
Cycle Efficiency

This paper continues the computational invcstigalion of optimum performance of a gas turbine configuration incorporating a gas generator, previously reported by the authors. Even for contemporary pressure ratios not previously considered, there appears to be no advantage in prebleeding the coolant air, and within the range considered, as previously found, the amount of coolant preheating has only a secondary effect on maximum engine efficiency. This is also true of the influence of allowable mean blade temperature on maximum engine efficiency, but both factors do have a pronounced effect on the optimum coolant and where maximum cycle efficiency is primarily determined by compressor pressure ratio and component isen-tropic efficiencies. The specific work output is confirmed under optimum conditions to be an almost linear function of the compressor turbine inlet temperature.

Proposal of Innovative Gas Turbine Combined Cycle Power Generation System

2004 ◽  
Author(s):  
Hideto Moritsuka
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Generation System ◽  
Turbine Inlet Temperature ◽  
Turbine Inlet ◽  
Power Generation System

In order to estimate the possibility to improve thermal efficiency of power generation use gas turbine combined cycle power generation system, benefits of employing the advanced gas turbine technologies proposed here have been made clear based on the recently developed 1500C-class steam cooling gas turbine and 1300C-class reheat cycle gas turbine combined cycle power generation systems. In addition, methane reforming cooling method and NO reducing catalytic reheater are proposed. Based on these findings, the Maximized efficiency Optimized Reheat cycle Innovative Gas Turbine Combined cycle (MORITC) Power Generation System with the most effective combination of advanced technologies and the new devices have been proposed. In case of the proposed reheat cycle gas turbine with pressure ratio being 55, the high pressure turbine inlet temperature being 1700C, the low pressure turbine inlet temperature being 800C, combined with the ultra super critical pressure, double reheat type heat recovery Rankine cycle, the thermal efficiency of combined cycle are expected approximately 66.7% (LHV, generator end).

A 2000-HP Military Vehicle Gas Turbine: A Study of Significant Thermodynamic and Mechanical Parameters

1968 ◽  
Author(s):  
A. F. Carter
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Overall Design ◽  
Blade Cooling ◽  
Turbine Inlet ◽  
Military Vehicle ◽  
Compressor Pressure Ratio ◽  
Selection Of

During a study of possible gas turbine cycles for a 2000-hp unit for tank propulsion, it has been established that the level of achievable specific fuel consumption (sfc) is principally determined by the combustor inlet temperature. If a regenerative cycle is selected, a particular value of combustor inlet temperature (and hence sfc) can be produced by an extremely large number of combinations of compressor pressure ratio, turbine inlet temperature, and heat exchanger effectiveness. This paper outlines the overall design considerations which led to the selection of a relatively low pressure ratio engine in which the turbine inlet temperature was sufficiently low that blade cooling was not necessary.

A Study of Steam-Cooled Humidified Gas Turbine Cycles

2011 ◽  
Author(s):  
Ching-Jen C. J. Tang
Keyword(s):  
Gas Turbine ◽  
Power Output ◽  
Pressure Ratio ◽  
Combustion Stability ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Electrical Efficiency ◽  
Percentage Points ◽  
Steam Cooling ◽  
Power Outputs

Humidified Gas Turbine (HGT) cycles such as the Evaporative Gas Turbine (EGT) and the Steam-Injected Gas Turbine (STIG) using humid air as the working medium do not require a complete steam turbine bottoming cycle; thus, their initial capital costs are not as high as those for the conventional combined cycles. The performance of a HGT cycle could be comparable to a state-of-the-art combined cycle for small loads. The availability of the steam from a HGT cycle presents opportunities for designing steam-cooled blades. Since the specific heat capacity for steam is higher than that for air, steam could potentially be a better coolant for turbine blades than air, resulting in higher cycle efficiency. In this study, three known HGT cycles are evaluated in terms of their electrical efficiencies and power outputs: the STIG, the Part-flow Evaporative Gas Turbine (PEvGT), and the combined STIG cycles. All the three HGT cycles are analyzed in two cooling options: steam and air coolings. The HGT cycles will be evaluated using consistent thermodynamic properties and assumptions. Like a simple gas turbine cycle, the HGT cycles are based on the well-known Brayton cycle whose performance is dictated by the cycle pressure ratio and turbine inlet temperature. Therefore, the electrical efficiencies and power outputs of the HGT cycles will be calculated as a function of the cycle pressure ratio and turbine inlet temperature. The steam-cooled cycles provide advantages over the air-cooled cycles in the electrical efficiency, power output, and combustion stability. The steam cooling improves the electrical efficiency by approximately 1.4 percentage points for the STIG cycle, by approximately 1.7 percentage points for the PEvGT cycle, and by approximately 1 percentage point for the combined STIG cycle. The maximum electrical efficiency of the steam-cooled PEvGT cycle is 54.6%, only 0.2 percentage points higher than that for the steam-cooled combined STIG cycle. The steam cooling generally results in more power output than the air cooling does for all the HGT cycles at most operating conditions. In addition, the steam cooling reduces the water content of the humid air entering the combustor, leading to significantly improved combustion stability.

scholarly journals Implementation of Adaptive Neuro-fuzzy Model to Optimize Operational Process of Multiconfiguration Gas-Turbines

2020 ◽  
Vol 2020 ◽  
pp. 1-17
Author(s):  
Chao Deng ◽  
Ahmed N. Abdalla ◽  
Thamir K. Ibrahim ◽  
MingXin Jiang ◽  
Ahmed T. Al-Sammarraie ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Power Output ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Operating Conditions ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Anfis Model ◽  
Neuro Fuzzy ◽  
Compressor Efficiency

In this article, the adaptive neuro-fuzzy inference system (ANFIS) and multiconfiguration gas-turbines are used to predict the optimal gas-turbine operating parameters. The principle formulations of gas-turbine configurations with various operating conditions are introduced in detail. The effects of different parameters have been analyzed to select the optimum gas-turbine configuration. The adopted ANFIS model has five inputs, namely, isentropic turbine efficiency (Teff), isentropic compressor efficiency (Ceff), ambient temperature (T1), pressure ratio (rp), and turbine inlet temperature (TIT), as well as three outputs, fuel consumption, power output, and thermal efficiency. Both actual reported information, from Baiji Gas-Turbines of Iraq, and simulated data were utilized with the ANFIS model. The results show that, at an isentropic compressor efficiency of 100% and turbine inlet temperature of 1900 K, the peak thermal efficiency amounts to 63% and 375 MW of power resulted, which was the peak value of the power output. Furthermore, at an isentropic compressor efficiency of 100% and a pressure ratio of 30, a peak specific fuel consumption amount of 0.033 kg/kWh was obtained. The predicted results reveal that the proposed model determines the operating conditions that strongly influence the performance of the gas-turbine. In addition, the predicted results of the simulated regenerative gas-turbine (RGT) and ANFIS model were satisfactory compared to that of the foregoing Baiji Gas-Turbines.

Research and Development of 300kW Class Ceramic Gas Turbine (Development of the Static Ceramic Components for CGT303)

1995 ◽  
Author(s):  
Mitsuharu Murota ◽  
Issei Ohhashi ◽  
Yoshiyuki Ito ◽  
Sadao Arakawa
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Pressure Ratio ◽  
Important Task ◽  
Inlet Temperature ◽  
Gas Temperature ◽  
Turbine Inlet Temperature ◽  
Engine Operation ◽  
Heat Cycle ◽  
Ceramic Components

As the result of setting the low pressure ratio at 4.5, sizes of the static ceramic components forming the gas passage in CGT303 have been increased, and establishing reliability of these components was thought to be the most important task. So, the heat-cycle tests were conducted, in advance of the engine operation, and improvements have been made on their material and constructions. After conducting 600 times of the heat-cycle tests, so far, up to the gas temperature of 1200°C, we have succeeded in the engine operation at the turbine inlet temperature of 1200°C Examples of the problems encountered in the test and of the solutions therefore are introduced in this paper.

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