Component Testing and Prototype Commissioning of MAN’s New Gas Turbine in the 6 MW-Class

2012 ◽  
Author(s):  
Alexander Wiedermann ◽  
Ulrich Orth ◽  
Emil Aschenbruck ◽  
Frank Reiss ◽  
Dietmar Krüger ◽  
...  
Keyword(s):  
Power Generation ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
High Precision ◽  
Test Field ◽  
Precision Engineering ◽  
Technical Parameters ◽  
Component Testing ◽  
High Standards ◽  
And Performance

MAN Diesel & Turbo has developed a new gas turbine in the 6 MW-class for both mechanical drive and power generation applications. The lay-out of the Gas Turbine has been driven by opportunities in current and future markets and the positioning of the competition, and this has determined the characteristics and technical parameters which have been optimized in the 6 MW design. The design makes use of extremely high precision engineering so that the assembly of sub components to modules is a smooth flowing process and can guarantee both the high standards in quality and performance which MAN Diesel & Turbo is aiming for. Individual components have been tested and thoroughly validated. These tests include in particular the compressor of the gas turbine and the combustion chamber. The commissioning of the gas turbine prototype engine had been prepared with a numerous number of measuring probes and carried out at the Oberhausen plant gas turbine test field. Results of component and the gas turbine prototype tests will be presented and discussed.

Design, Evaluation and Performance Analysis of Staged Low Emission Combustors

2012 ◽  
Author(s):  
Gajanana B. Hegde ◽  
Bhupendra Khandelwal ◽  
Vishal Sethi ◽  
Riti Singh
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Design Methodology ◽  
Reverse Flow ◽  
Axial Flow ◽  
Design Procedure ◽  
Extensive Study ◽  
Theoretical Design ◽  
Low Emission ◽  
And Performance

The most uncertain and challenging part in the design of a gas turbine has long been the combustion chamber. There has been large number of experimentations in industries and universities alike to better understand the dynamic and complex processes that occur inside a combustion chamber. This study concentrates on gas turbine combustors as a whole, and formulates a theoretical design procedure for staged combustors in particular. Not much of literatures available currently in public domain provide intensive study on designing staged combustors. The work covers an extensive study of design methods applied in conventional combustor designs, which includes the reverse flow combustor and the axial flow annular combustors. The knowledge acquired from this study is then applied to develop a theoretical design methodology for double staged (radial and axial) low emission annular combustors. Additionally a model combustor is designed for each type; radial and axial staging using the developed methodology. A prediction of the performance for the model combustors is executed. The main conclusion is that the dimensions of model combustors obtained from the developed design methodology are within the feasibility limits. The comparison between the radially staged and the axially staged combustor has yielded the predicted results such as lower NOx prediction for the latter and shorter combustor length for the former. The NOx emission result of the new combustor models are found to be in the range of 50–60ppm. However the predicted NOx results are only very crude and need further detailed study.

A Study of Humidified Gas Turbines for Short-Term Realization in Midsized Power Generation—Part I: Nonintercooled Cycle Analysis

2005 ◽  
Vol 127 (1) ◽  
pp. 91-99 ◽  
Author(s):  
Michael A. Bartlett ◽  
Mats O. Westermark
Keyword(s):  
Power Generation ◽  
Economic Analysis ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Heat Recovery ◽  
Performance Potential ◽  
Short Term ◽  
And Performance ◽  
Working Media

Humidified Gas Turbine (HGT) cycles are a group of advanced gas turbine cycles that use water-air mixtures as the working media. In this article, three known HGT configurations are examined in the context of short-term realization for small to midsized power generation: the Steam Injected Gas Turbine, the Full-flow Evaporative Gas Turbine, and the Part-flow Evaporative Gas Turbine. The heat recovery characteristics and performance potential of these three cycles are assessed, with and without intercooling, and a preliminary economic analysis is carried out for the most promising cycles.

Fine Tuning and Detailed Testing of a New Heavy Duty G.T. in the Field

1975 ◽  
Author(s):  
C. P. Lerch ◽  
P. H. Wulff
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Exhaust Emissions ◽  
Fine Tuning ◽  
Heavy Duty ◽  
Evaluation Program ◽  
Chamber Design ◽  
Site Evaluation ◽  
And Performance

Final field adjustments to optimize combustion and performance, as well as the comprehensive on site evaluation program performed on this gas turbine, are described in this paper. Included are a description of a series of minor combustion modifications which were easily possible due to the unique single-combustion-chamber design. Tests discussed included measurements of turbine blade operating temperatures and exhaust emissions.

Exergoeconomic analysis and performance assessment of selected gas turbine power plants

2015 ◽  
Vol 12 (3) ◽  
pp. 283-300 ◽  
Author(s):  
S.O. Oyedepo ◽  
R.O. Fagbenle ◽  
S.S. Adefila ◽  
Md. Mahbub Alam
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Power Plants ◽  
Exergy Analysis ◽  
Unit Cost ◽  
Exergy Destruction ◽  
Improvement Potential ◽  
And Performance ◽  
Exergoeconomic Analysis ◽  
The Cost

In this study, exergoeconomic analysis and performance evaluation of selected gas turbine power plants in Nigeria were carried out. The study was conducted using operating data obtained from the power plants to determine the exergy efficiency, exergy destruction, unit cost of electricity and cost of exergy destruction of the major components of a gas turbine engine in the selected power plants. The results of exergy analysis confirmed that the combustion chamber is the most exergy destructive component compared to other cycle components as expected. The total efficiency defects and overall exergetic efficiency of the selected power plants vary from 38.64 to 69.33% and 15.66 to 30.72% respectively. The exergy analysis further shows that the exergy improvement potential of the selected plants varies from 54.04 MW to 159.88 MW. The component with the highest exergy improvement potential is the combustion chamber and its value varies from 30.21 MW to 88.86 MW. The results of exergoeconomic analysis show that the combustion chamber has the greatest cost of exergy destruction compared to other components. Increasing the gas turbine inlet temperature (GTIT), both the exergy destruction and the cost of exergy destruction of this component were found to decrease. The results of this study revealed that an increase in the GTIT of about 200 K can lead to a reduction of about 29% in the cost of exergy destruction. From exergy costing analysis, the unit cost of electricity produced in the selected power plants varies from cents 1.99 /kWh (N3.16 /kWh) to cents 5.65 /kWh (N8.98 /kWh).

Effect on Temperature Distribution at Liner Wall for Different Equivalence Ratios of Primary Zone for Small Capacity Gas Turbine Combustion Chamber

2005 ◽  
Author(s):  
Digvijay B. Kulshreshtha ◽  
S. A. Channiwala ◽  
Jatin R. Patel
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Systematic Approach ◽  
Combustion Chambers ◽  
Experimental Optimization ◽  
Primary Zone ◽  
Different Types ◽  
And Performance ◽  
Critical Components ◽  
Small Capacity

The combustion chamber of gas turbine unit is one of the most critical components to be designed. The study of literature review reveals that much work is available pertaining to design and performance of combustion chamber. However, the systematic approach and optimized liner wall configuration is not easily traceable in the literature. This is particularly true for small capacity units. Hence there is a need for experimental optimization of combustion chamber in small capacity range. The present work aims at the experimental optimization of liner wall configuration. Four different types of combustion chambers with primary zone equivalence ratios of 0.5, 0.7, 0.9 and 1.1 are designed, developed and experimented based on which an optimal configuration is recommended. It is worth to mention that the present work clearly focuses the combustion chamber with equivalence ratio in primary zone as 0.9 as the optimal combustion chamber.

Combustion chamber design and performance for micro gas turbine application

2017 ◽  
Vol 166 ◽  
pp. 258-268 ◽  
Author(s):  
Ibrahim I. Enagi ◽  
K.A. Al-attab ◽  
Z.A. Zainal
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Micro Gas Turbine ◽  
Chamber Design ◽  
And Performance

Numerical Analysis of Biomass-Derived Gaseous Fuels Fired in a RQL Micro Gas Turbine Combustion Chamber: Preliminary Results

2011 ◽  
Author(s):  
Paolo Laranci ◽  
Edoardo Bursi ◽  
Francesco Fantozzi
Keyword(s):  
Power Generation ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Carbon Dioxide Emissions ◽  
Gas Turbines ◽  
Landfill Gas ◽  
Pyrolysis Gas ◽  
Micro Gas Turbine ◽  
Gaseous Fuels ◽  
Reduce Carbon Dioxide

The economically sustainable availability of biomass residuals and the growing need to reduce carbon dioxide emissions from power generation facilities has driven the development of a series of processes that lead to the production of a variety of biomass-derived fuels gaseous fuels, such as syngas, pyrolysis gas, landfill gas and digester gas. These technologies can find an ideal coupling when used for fuelling micro gas turbines, especially for distributed power generation applications, in a range between 50 and 500 kWE. This paper features a report on numerical activity carried out at the University of Perugia on a 80 kWE micro gas turbine annular combustion chamber, featuring RQL technology, that has been numerically modeled in order to verify combustion requirements, principally in terms of air/fuel ratio and lower heating value, simulating mixtures with varying chemical composition. The use of CFD turbulence and combustion modeling, via both Eddy Break-up and non-adiabatic PPDF methods, allows us to evaluate flame temperatures and stability, NOx and unburnt hydrocarbons emissions, under various load conditions, for the different fuel mixtures taken into account.

Design, Evaluation and Performance Analysis of Staged Low Emission Combustors

2014 ◽  
Vol 136 (10) ◽  
Author(s):  
Bhupendra Khandelwal ◽  
Olamilekan Banjo ◽  
Vishal Sethi
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Design Methodology ◽  
Reverse Flow ◽  
Axial Flow ◽  
Design Procedure ◽  
Extensive Study ◽  
Theoretical Design ◽  
Low Emission ◽  
And Performance

The most uncertain and challenging part in the design of a gas turbine has long been the combustion chamber. There has been a large number of experimentations in industry and universities alike to better understand the dynamic and complex processes that occur inside a combustion chamber. This study concentrates on gas turbine combustors, as a whole, and formulates a theoretical design procedure for staged combustors, in particular. Not much of the literature currently available in the public domain provides intensive study on designing staged combustors. The work covers an extensive study of the design methods applied in conventional combustor designs, which includes the reverse flow combustor and the axial flow annular combustors. The knowledge acquired from this study is then applied to develop a theoretical design methodology for double staged (radial and axial) low emission annular combustors. Additionally, a model combustor is designed for each type, radial and axial, of staging using the developed methodology. A prediction of the performance of the model combustors is executed. The main conclusion is that the dimensions of the model combustors obtained from the developed design methodology are within the feasibility limits. The comparison between the radially staged and the axially staged combustor has yielded the predicted results such as a lower NOx prediction for the latter and a shorter combustor length for the former. The NOx emission results of the new combustor models are found to be in the range of 50–60 ppm. However, the predicted NOx results are only very crude and need further detailed study.

Innovative Concepts for Auxiliary Power Generation on USN Ships

1988 ◽  
Author(s):  
Thomas L. Bowen ◽  
Jon C. Ness
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Simple Cycle ◽  
Turbine Plant ◽  
Advantages And Disadvantages ◽  
Auxiliary Power ◽  
Alternative Approaches ◽  
Gas Turbine Plant ◽  
And Performance ◽  
Generator Sets

Auxiliary power generation to satisfy demands for electricity and pressurized air onboard naval ships represents a significant impact on the ship’s design and performance. These demands are continually growing as newer ships require improved capabilities and shipboard systems become more complex. This paper briefy examines options to the present use of multiple, simple-cycle, gas-turbine-driven generator sets on U.S. Navy destroyers and cruisers. Improved engines for ship service generator drive applications are considered which are presently available from industry or are adapations of presently available engines. The feasibility of producing an auxiliary gas turbine from components taken from an intercooled-recuperative propulsion gas turbine is examined, as well as an integrated gas turbine plant which allows auxiliary power to be supplied as power takeoff from the propulsion gas turbine. The paper describes some of the design and performance aspects of these alternative approaches as well as some of their advantages and disadvantages.

Field Evaluation and Operating Experience of the Allison 501-KB5 Industrial Gas Turbine

1986 ◽  
Author(s):  
John A. Latcovich ◽  
Charles S. Bach
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Operating Experience ◽  
Performance Testing ◽  
Field Evaluation ◽  
Low Risk ◽  
Technical Approach ◽  
And Performance ◽  
One Year ◽  
Industrial Gas Turbine

The Allison 501-KB5 3924 KW gas turbine was introduced to the industrial power generation market in 1982 as a low risk upgrade of the 501-KB engine. The aero-derivative and industrial background of the 501-KB engine is discussed along with the technical approach, engine features and performance (20% more power and 6% less fuel than the 501-KB) of the upgrade. The results of a one year field evaluation of an early 501-KB5 engine are presented, including performance testing and teardown inspections conducted after the evaluation. Since introduction in 1982, fifty-five production 501-KB5 engines have been delivered, and the operating experience of these engines, which now exceeds 230,000 hours is presented.

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