Application of Bio-fAEG: A Biofouling Assessment Model in Gas Turbines and the Effect of Degraded Fuels on Engine Performance Simulations

2015 ◽  
Author(s):  
Tosin Onabanjo ◽  
Giuseppina Di Lorenzo ◽  
Theoklis Nikolaidis ◽  
Yinka Somorin
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Computational Study ◽  
Engine Performance ◽  
Heat Rate ◽  
Significant Loss ◽  
Assessment Model ◽  
Gas Temperature ◽  
Performance Simulation ◽  
Exhaust Gas Temperature

The recent advances for flexible fuel operation and the integration of biofuels and blends in gas turbines raise concern on engine health and quality. One of such potential threats involves the contamination and the growth of microorganisms in fuels and fuel systems with consequential effect on engine performance and health. In the past, the effects of microbial growth in fuels have been qualitatively described; however their effects in gas turbines have not necessarily been quantified. In this paper, the effects of fuel deterioration are examined on a simulated aero-derivative gas turbine. A diesel-type fuel comprising of thirteen (13) hydrocarbon fractions was formulated and degraded with Bio-fAEG, a bio fouling assessment model that defines degraded fuels for performance simulation and analysis, predicts biodegradation rates as well as calculates the amount of water required to initiate degradation under aerobic conditions. The degraded fuels were integrated in the fuel library of Turbomatch (v2.0) and a twin shaft gas turbine was modeled for fuel performance analysis. The results indicate a significant loss in performance with reduced thermal efficiency of 1% and 10.4% and increased heat rate of 1% and 11.6% for the use of 1% and 10% degraded fuels respectively. Also parameters such as exhaust gas temperature and mass flow deviated from the baseline data indicating potential impact on engine health. Therefore, for reliable and safe operation, it is important to ensure engines run on good quality of fuel. This computational study provides insights on fuel deterioration in gas turbines and how it affects engine health.

World’s First LM5000 to LM6000 Cogeneration Plant Repowering

2000 ◽  
Author(s):  
Michael T. McCarrick ◽  
Robert K. Rosencrance
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Heat Rate ◽  
Economic Benefits ◽  
Production Model ◽  
Cogeneration Plant ◽  
Gas Temperature ◽  
Energy Facility ◽  
Current Production ◽  
Exhaust Gas Temperature

With the introduction of GE’s latest and most efficient gas turbine, the LM6000 in 1992, and the end of production of GE’s LM5000 gas turbine in 1997, the concept of repowering aging LM5000 gas turbine powered cogeneration plants with LM6000 gas turbines was an idea that most LM5000 owners and operators dreamed about. The LM6000 is an ideal replacement for the LM5000 as they both have nearly the same mass flow and exhaust gas temperature (critical for Heat Recovery Steam Generator (HRSG) compatibility), are about the same physical weight and dimensions, and can be operated in the same power range. Also, as the LM6000 is a current production model, it has more readily available spare gas turbines and turbine parts, has a much improved heat rate, lower emissions level, and has an option (SPRINT), for added power. In December 1999, the UAE Oildale Energy Facility became the first plant to operate with a newly installed LM6000 in its former LM5000 package. (This March the second LM5000 to LM6000 repowering was completed for Calpine Corporation at their Greenleaf #1 Cogeneration Plant in Yuba City, CA.) Energy Services, Inc., GE’s authorized LM6000 repowering OEM, designed, engineered and project managed the repowering. This paper will present the reasons UAE decided to repower; discuss the technical challenges encountered with, and modifications made to, the GEC ELM-150 cogeneration plant to accommodate the LM6000; review the schedule; and provide the economic benefits of the improved heat rate and reliability of the LM6000.

Analysis of Operational Effects on Cooled H-Class Gas Turbines

2019 ◽  
Author(s):  
Selcuk Can Uysal ◽  
James B. Black
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Power Output ◽  
Thermal Efficiency ◽  
Gas Turbines ◽  
Cooling System ◽  
Engine Performance ◽  
Heat Rate ◽  
Operating Conditions ◽  
Performance Parameters

Abstract During the operation of an industrial gas turbine, the engine deviates from its new condition performance because of several effects including dirt build-up, compressor fouling, material erosion, oxidation, corrosion, turbine blade burning or warping, thermal barrier coating (TBC) degradation, and turbine blade cooling channel clogging. Once these problems cause a significant impact on engine performance, maintenance actions are taken by the operators to restore the engine to new performance levels. It is important to quantify the impacts of these operational effects on the key engine performance parameters such as power output, heat rate and thermal efficiency for industrial gas turbines during the design phase. This information can be used to determine an engine maintenance schedule, which is directly related to maintenance costs during the anticipated operational time. A cooled gas turbine performance analysis model is used in this study to determine the impacts of the TBC degradation and compressor fouling on the engine performance by using three different H-Class gas turbine scenarios. The analytical tool that is used in this analysis is the Cooled Gas Turbine Model (CGTM) that was previously developed in MATLAB Simulink®. The CGTM evaluates the engine performance using operating conditions, polytropic efficiencies, material properties and cooling system information. To investigate the negative impacts on engine performance due to structural changes in TBC material, compressor fouling, and their combined effect, CGTM is used in this study for three different H-Class engine scenarios that have various compressor pressure ratios, turbine inlet temperatures, and power and thermal efficiency outputs; each determined to represent different classes of recent H-Class gas turbines. Experimental data on the changes in TBC performance are used as an input to the CGTM as a change in the TBC Biot number to observe the impacts on engine performance. The effect of compressor fouling is studied by changing the compressor discharge pressures and polytropic compressor efficiencies within the expected reduction ranges. The individual and combined effects of compressor fouling and TBC degradation are presented for the shaft power output, thermal efficiency and heat rate performance parameters. Possible improvements for the designers to reduce these impacts, and comparison of the reductions in engine performance parameters of the studied H-Class engine scenarios are also provided.

Early fault detection of gas turbine hot components under different ambient and operating conditions

2021 ◽  
pp. 095441002098689
Author(s):  
Jiao Liu ◽  
Jinfu Liu ◽  
Daren Yu ◽  
Zhongqi Wang ◽  
Weizhong Yan ◽  
...  
Keyword(s):  
Fault Detection ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Detection Method ◽  
Operating Conditions ◽  
Exhaust Gas ◽  
Gas Temperature ◽  
Spatial Correlations ◽  
Early Fault Detection ◽  
Exhaust Gas Temperature

Failure of hot components in gas turbines often causes catastrophic results. Early fault detection can prevent serious incidents and improve the availability. A novel early fault detection method of hot components is proposed in this article. Exhaust gas temperature is usually used as the indicator to detect the fault in the hot components, which is measured by several exhaust thermocouples with uniform distribution at the turbine exhaust section. The healthy hot components cause uniform exhaust gas temperature (EGT) profile, whereas the hot component faults could cause the uneven EGT profile. However, the temperature differences between different thermocouple readings are also affected by different ambient and operating conditions, and it sometimes has a greater influence on EGT than the faults. In this article, an accurate EGT model is presented to eliminate the influence of different ambient and operating conditions on EGT. Especially, the EGT profile swirl under different ambient and operating conditions is also included by considering the information of the thermocouples’ spatial correlations and the EGT profile swirl angle. Based on the developed EGT model, the detection performance of early fault detection of hot components in gas turbine is improved. The accuracy and effectiveness of the developed early fault detection method are evaluated by the real-world gas turbine data.

Gas Turbine Power Augmentation Technologies: A Systematic Comparative Evaluation Approach

2010 ◽  
Author(s):  
M. Bianchi ◽  
L. Branchini ◽  
A. De Pascale ◽  
F. Melino ◽  
A. Peretto ◽  
...  
Keyword(s):  
Ambient Temperature ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Comparative Evaluation ◽  
Fuel Efficiency ◽  
Heat Rate ◽  
Steam Injection ◽  
Significant Loss ◽  
Evaluation Approach ◽  
Auxiliary Power

Increasing electric rates in peak demand period, especially during summer months, are forcing power producers to look for gas turbine power augmentation technologies (PATs). One of the major undesirable features of all the gas turbines is that their power output and fuel efficiency decreases with increase in the ambient temperature resulting in significant loss in revenues particularly during peak hours. This paper presents a systematic comparative evaluation approach for various gas turbine power augmentation technologies (PATs) available in the market. The application of the discussed approach has been demonstrated by considering two commonly used gas turbine designs, namely, heavy-duty industrial and aeroderivative. The following PATs have been evaluated: inlet evaporative, inlet chilling, high pressure fogging, overspray, humid air injection and steam injection. The main emphasis of this paper is to provide a detailed comparative thermodynamic analysis of the considered PATs including the main variables, such as ambient temperature and relative humidity, which influence their performance in terms of power boost, heat rate reduction and auxiliary power consumption.

scholarly journals Gas Turbine Inlet Air Cooling and the Effect on a Westinghouse 501D5 CT

1995 ◽  
Author(s):  
Chuck Kohlenberger
Keyword(s):  
Gas Turbine ◽  
Mass Flow ◽  
Heat Rate ◽  
International Standards ◽  
Air Cooling ◽  
Exhaust Gas ◽  
Gas Temperature ◽  
Turbine Inlet ◽  
Air Temperatures ◽  
Exhaust Gas Temperature

The temperature of the air entering a gas turbine prime mover has a dramatic effect on its performance, including output, heat rate, and exhaust gas temperature (EGT). These variations are easily observed in actual operation and by reference to generic gas turbine (GT) performance curves. The gross capacity increase of a GT operating at 40F (8C) inlet compared to operation at 102F (70C) is 28%. The gross reduction in heat rate for this 62F (16.7C) differential is 6%, and the exhaust gas temperature is reduced 5%. Since the overall mass flow through the GT is increased through the cooling process, the added energy available in the heat recovery steam generator (HRSG), is increased 8% The significant improvements in GT output and efficiency which can be achieved by maintaining lower inlet air temperatures encourage the manufacturer, systems engineer, owner, and operator of GT facilities to consider seriously the implementation of a gas turbine inlet air cooling (GTIAC) system. GTIAC systems have proven to produce some very excellent economic paybacks due to increased power output, EG mass flow, and reduced heat rates. Generic gross performance factors are plotted (See Figure 1) against inlet air temperature compared to International Standards Organization (ISO) conditions.

A Gas Turbine Performance Simulation Program and Its Application to an IGCC Gas Turbine

2010 ◽  
Author(s):  
Jong Jun Lee ◽  
Young Sik Kim ◽  
Tong Seop Kim ◽  
Jeong Lak Sohn ◽  
Yong Jin Joo
Keyword(s):  
Gas Turbine ◽  
System Integration ◽  
Gas Turbines ◽  
Engine Performance ◽  
Operating Conditions ◽  
Simulation Program ◽  
Component Level ◽  
Performance Simulation ◽  
Blade Cooling ◽  
Variable Stator

This paper explains a performance simulation program for power generation gas turbines and its application to an IGCC gas turbine. The program has a modular structure and both the stage-level and entire component-level models were adopted. Stage-by-stage calculations were used in the compressor and the turbine. In particular, the compressor module is based on a stage-stacking method and is capable of simulating the effect of variable stator vanes. The combustor model has the capability of dealing with various fuels including syngas. The turbine module is capable of estimating blade cooling performance. The program can be easily extended to other applied cycles such as recuperated and reheated cycles because the program structure is fully modular. The program was verified for simple cycle commercial engines. In addition, the program was applied to the gas turbine in an IGCC plant. Influences of major system integration parameters on the operating conditions of the compressor and turbine as well as on engine performance were analyzed.

scholarly journals Analysis of an Integrated Solar Combined Cycle with Recuperative Gas Turbine and Double Recuperative and Double Expansion Propane Cycle

Entropy ◽  
2020 ◽  
Vol 22 (4) ◽  
pp. 476
Author(s):  
Antonio Rovira ◽  
Rubén Abbas ◽  
Marta Muñoz ◽  
Andrés Sebastián
Keyword(s):  
Gas Turbine ◽  
Heat Rate ◽  
Rankine Cycle ◽  
Combined Cycle ◽  
Heat Transfer Fluid ◽  
Working Fluid ◽  
Gas Temperature ◽  
Cost Of Energy ◽  
Exhaust Gas Temperature ◽  
Solar Field

The main objective of this paper is to present and analyze an innovative configuration of integrated solar combined cycle (ISCC). As novelties, the plant includes a recuperative gas turbine and the conventional bottoming Rankine cycle is replaced by a recently developed double recuperative double expansion (DRDE) cycle. The configuration results in a fuel saving in the combustion chamber at the expense of a decreased exhaust gas temperature, which is just adequate to feed the DRDE cycle that uses propane as the working fluid. The solar contribution comes from a solar field of parabolic trough collectors, with oil as the heat transfer fluid. The optimum integration point for the solar contribution is addressed. The performance of the proposed ISCC-R-DRDE design conditions and off-design operation was assessed (daily and yearly) at two different locations. All results were compared to those obtained under the same conditions by a conventional ISCC, as well as similar configurations without solar integration. The proposed configuration obtains a lower heat rate on a yearly basis in the studied locations and lower levelized cost of energy (LCOE) than that of the ISCC, which indicates that such a configuration could become a promising technology.

Shop Test Result of the V64.3 Gas Turbine

1992 ◽  
Vol 114 (4) ◽  
pp. 676-681 ◽  
Author(s):  
M. Jansen ◽  
T. Schulenberg ◽  
D. Waldinger
Keyword(s):  
Gas Turbines ◽  
Full Range ◽  
Engine Performance ◽  
Combined Cycle ◽  
Fuel Oil ◽  
Test Facility ◽  
Gas Temperature ◽  
Operation Conditions ◽  
Performance Results ◽  
Exhaust Gas Temperature

The V64.3 60-MW combustion turbine is the first of a new generation of high-temperature gas turbines, designed for 50 and 60 Hz simple cycle, combined cycle, and cogeneration applications. The prototype engine was tested in 1990 in the Berlin factories under the full range of operation conditions. It was equipped with various measurement systems to monitor pressures, gas and metal temperatures, clearances, strains, vibrations, and exhaust emissions. The paper describes the engine design, the test facility and instrumentation, and the engine performance. Results are given for turbine blade temperatures, compressor and turbine vibrations, exhaust gas temperature, and NOx emissions for combustion of natural gas and fuel oil.

scholarly journals Shop Test Result of V64.3 Gas Turbine

1991 ◽  
Author(s):  
M. Jansen ◽  
T. Schulenberg ◽  
D. Waldinger
Keyword(s):  
Gas Turbines ◽  
Full Range ◽  
Engine Performance ◽  
Combined Cycle ◽  
Fuel Oil ◽  
Test Facility ◽  
Gas Temperature ◽  
Operation Conditions ◽  
Performance Results ◽  
Exhaust Gas Temperature

The V64.3 60MW combustion turbine is the first of a new generation of high temperature gas turbines, designed for 50 and 60Hz simple cycle, combined cycle and cogeneration applications. The prototype engine was tested in 1990 in the Berlin factories under the full range of operation conditions. It was equipped with various measurement systems to monitor pressures, gas and metal temperatures, clearences, strains, vibrations, and exhaust emissions. The paper describes the engine design, the test facility and instrumentation, and the engine performance. Results are given for turbine blade temperatures, compressor and turbine vibrations, exhaust gas temperature, and NOx emissions for combustion of natural gas and fuel oil.

Numerical investigation of non-uniform flow in twin-silo combustors and impact on axial turbine stage performance

2021 ◽  
pp. 095765092199394
Author(s):  
Hafiz M Hassan ◽  
Adeel Javed ◽  
Asif H Khoja ◽  
Majid Ali ◽  
Muhammad B Sajid
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Internal Flow ◽  
Large Temperature ◽  
Clear Understanding ◽  
Gas Temperature ◽  
Turbine Stage ◽  
Flow Angle ◽  
Axial Turbine ◽  
Stage Performance

A clear understanding of the flow characteristics in the older generation of industrial gas turbines operating with silo combustors is important for potential upgrades. Non-uniformities in the form of circumferential and radial variations in internal flow properties can have a significant impact on the gas turbine stage performance and durability. This paper presents a comprehensive study of the underlying internal flow features involved in the advent of non-uniformities from twin-silo combustors and their propagation through a single axial turbine stage of the Siemens v94.2 industrial gas turbine. Results indicate the formation of strong vortical structures alongside large temperature, pressure, velocity, and flow angle deviations that are mostly located in the top and bottom sections of the turbine stage caused by the excessive flow turning in the upstream tandem silo combustors. A favorable validation of the simulated exhaust gas temperature (EGT) profile is also achieved via comparison with the measured data. A drop in isentropic efficiency and power output equivalent to 2.28% points and 2.1 MW, respectively is observed at baseload compared to an ideal straight hot gas path reference case. Furthermore, the analysis of internal flow topography identifies the underperforming turbine blading due to the upstream non-uniformities. The findings not only have implications for the turbine aerothermodynamic design, but also the combustor layout from a repowering perspective.

Sign in / Sign up

Export Citation Format

Share Document