scholarly journals Erratum: “The Design and Development of an Advanced Heavy-Duty Gas Turbine” (Journal of Engineering for Gas Turbines and Power, 1988, 110, pp. 243–250)

1988 ◽  
Vol 110 (3) ◽  
pp. 562-562
Author(s):  
D. E. Brandt
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Heavy Duty ◽  
Design And Development ◽  
Heavy Duty Gas Turbine

Experience With Large Heavy-Duty Gas Turbine Rotors

1981 ◽  
Author(s):  
O. R. Schmoch ◽  
B. Deblon
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Rotor ◽  
Strength Properties ◽  
Operating Conditions ◽  
Material Strength ◽  
Heavy Duty ◽  
Turbine Rotors ◽  
Heavy Duty Gas Turbine ◽  
Response To Temperature

The peripheral speeds of the rotors of large heavy-duty gas turbines have reached levels which place extremely high demands on material strength properties. The particular requirements of gas turbine rotors, as a result of the cycle, operating conditions and the ensuing overall concepts, have led different gas turbine manufacturers to produce special structural designs to resolve these problems. In this connection, a report is given here on a gas turbine rotor consisting of separate discs which are held together by a center bolt and mutually centered by radial serrations in a manner permitting expansion and contraction in response to temperature changges. In particular, the experience gained in the manufacture, operation and servicing are discussed.

Three-Dimensional Time-Resolved Flow Field in the First and Last Turbine Stage of a Heavy Duty Gas Turbine: Part II — Interpretation of Blade Pressure Fluctuations

2000 ◽  
Author(s):  
Martin von Hoyningen-Huene ◽  
Wolfram Frank ◽  
Alexander R. Jung
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Fluctuations ◽  
Three Dimensional ◽  
Potential Interaction ◽  
Heavy Duty ◽  
Turbine Stage ◽  
Count Ratio ◽  
Heavy Duty Gas Turbine

Unsteady stator-rotor interaction in gas turbines has been investigated experimentally and numerically for some years now. Most investigations determine the pressure fluctuations in the flow field as well as on the blades. So far, little attention has been paid to a detailed analysis of the blade pressure fluctuations. For further progress in turbine design, however, it is mandatory to better understand the underlying mechanisms. Therefore, computed space–time maps of static pressure are presented on both the stator vanes and the rotor blades for two test cases, viz the first and the last turbine stage of a modern heavy duty gas turbine. These pressure fluctuation charts are used to explain the interaction of potential interaction, wake-blade interaction, deterministic pressure fluctuations, and acoustic waveswith the instantaneous surface pressure on vanes and blades. Part I of this two-part paper refers to the same computations, focusing on the unsteady secondary now field in these stages. The investigations have been performed with the flow solver ITSM3D which allows for efficient simulations that simulate the real blade count ratio. Accounting for the true blade count ratio is essential to obtain the correct frequencies and amplitudes of the fluctuations.

Protective Systems for Gas Turbines in Industry

1974 ◽  
Author(s):  
J. N. Shinn
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Comprehensive System ◽  
Heavy Duty ◽  
Protective System ◽  
System Philosophy ◽  
Heavy Duty Gas Turbine ◽  
Protective Systems

Modern heavy-duty gas turbine installations employ a comprehensive system of protective circuits to provide needed equipment protection without jeopardizing plant reliability. The design of these circuits and the overall protective system philosophy are discussed to illustrate how protection and reliability are maximized. Experience gained to date on the application of these protective circuits also is reviewed.

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.

Advanced Gas Turbine Technology: ABB/BBC Historical Firsts

2001 ◽  
Author(s):  
Dietrich Eckardt ◽  
Peter Rufli
Keyword(s):  
Power Generation ◽  
Environmental Impact ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Technology ◽  
Heavy Duty ◽  
Excellent Performance ◽  
Global Power ◽  
Heavy Duty Gas Turbine ◽  
Development Center

During more than 100 years engineers of the Swiss development center of A.-G. BBC Brown, Boveri & Cie., from 1988 onwards ABB Asea Brown Boveri Ltd, in 1999 ABB ALSTOM POWER Ltd and now ALSTOM Power Ltd in Baden, Switzerland have significantly contributed to the achievement of todays advanced gas turbine concept. Numerous “Firsts” are highlighted in this paper — ranging from the first realization of the industrial, heavy-duty gas turbine in the 1930s to todays high-technology Gas Turbine (GT) products, combining excellent performance, extraordinary low environmental impact with commercial attractiveness for global power generation. Interesting connections could be unveiled for the early parallel development of industrial and areo gas turbines.

scholarly journals MS 9001F: A New Advanced Technology 50 Hz Gas Turbine

1990 ◽  
Author(s):  
D. E. Brandt ◽  
M. Colas
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Aircraft Engine ◽  
Advanced Technology ◽  
Test Plan ◽  
Heavy Duty ◽  
Compressor Inlet ◽  
Design Characteristics ◽  
Heavy Duty Gas Turbine

Following a thorough market analysis, the MS 9001F heavy duty gas turbine has been designed using aerodynamic scaling based on the 60 Hz MS 7001F. Effort put into the design has been shared by the engineering departments of ALSTHOM and GE. This paper discusses the market surveys for large heavy duty gas turbines as well as the basis of design for the MS 9001F, which has been derived from the MS 7001F. Specifically discussed are the role of scaling, the design characteristics of the MS 7001F and the MS 9001F, the results of 7001F prototype testing, the test plan for the MS 9001F, plant lay out possibilities and ratings. The MS 9001F gas turbine uses advanced aircraft engine technology in its design, with a rating based on a firing temperature of 1260°C (2300°F), which is 156°C (280°F) higher and with compressor inlet flow 50% greater than its predecessor, the MS 9001E.

Three-Dimensional Time-Resolved Flow Field in the First and Last Turbine Stage of a Heavy Duty Gas Turbine: Part I — Secondary Flow Field

2000 ◽  
Author(s):  
Martin von Hoyningen-Huene ◽  
Wolfram Frank ◽  
Alexander R. Jung
Keyword(s):  
Flow Field ◽  
Secondary Flow ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Companion Paper ◽  
Heavy Duty ◽  
Turbine Stage ◽  
Time Resolved ◽  
Heavy Duty Gas Turbine ◽  
Secondary Flow Field

Unsteady stator-rotor interaction in gas turbines has been investigated both experimentally and numerically for some years now. Even though the numerical methods are still in development, today they have reached a certain degree of maturity allowing industry to focus on the results of the computations and their impact on turbine design, rather than on a further improvement of the methods themselves. The key to increase efficiency in modern gas turbines is a better understanding and subsequent optimization of the loss-generation mechanisms. A major part of these are the secondary losses. To this end, this paper presents the time-resolved secondary flow field for the two test cases computed, viz the first and the last turbine stage of a modern heavy duty gas turbine. A companion paper referring to the same computations focuses on the unsteady pressure fluctuations on vanes and blades. The investigations have been performed with the flow solver ITSM3D which allows for efficient calculations that simulate the real blade count ratio. This is a prerequisite to simulate the unsteady phenomena in frequency and amplitude properly.

The Treatment of Marine Heavy Fuels for Gas Turbine Combustion

1972 ◽  
Author(s):  
P. J. Cullen ◽  
T. A. Urbas
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Heavy Duty ◽  
Fuel Treatment ◽  
Gas Turbine Combustion ◽  
Heavy Fuels ◽  
Heavy Duty Gas Turbine

The resurgence of interest in the heavy duty gas turbine for marine use is due in a large part to its ability to burn residual and crude fuels. Generalities involving fuel treatment requirements have been bandied about for years and often the wrong information is used by unknowledgeable individuals when making quotations or bid evaluations. The purpose of this paper is to present firm information on the treatment of marine fuels for heavy duty gas turbines.

Redesign of the TG20 Heavy-Duty Gas Turbine to Increase Turbine Inlet Temperature and Global Efficiency

2020 ◽  
Author(s):  
Mirko Baratta ◽  
Francesco Cardile ◽  
Daniela Anna Misul ◽  
Nicola Rosafio ◽  
Simone Salvadori ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Coolant Fluid ◽  
Specific Power ◽  
Inlet Temperature ◽  
Heavy Duty ◽  
Turbine Inlet Temperature ◽  
Rotating Blade ◽  
Turbine Inlet ◽  
Heavy Duty Gas Turbine

Abstract The even more stringent limitations set by the European Commission on pollutant emissions are forcing gas turbine manufacturers towards the redesign of the most important components to increase efficiency and specific power. Current trends in gas turbine design include an increased attention to the design of cooling systems and enhanced best practices for the study of components interaction. At the same time, the recent crisis suffered by the oil and gas industry reduced the interest in brand new gas turbines, thus increasing the service market. Therefore, original equipment manufacturers would rather propose the replacement of specific components within the gas turbine plant during its maintenance with compatible elements that are likely to guarantee increased performance and longer residual lifetime at a more desirable nominal working point. In the present activity the cooling system of the TG20 heavy-duty gas turbine has been redesigned to increase the turbine inlet temperature while contemporaneously reducing the total amount of coolant mass-flow. Specifically, the cooling scheme of the rotating blade of the first turbine row has been reviewed at the Department of Energy (DENERG) of Politecnico di Torino in cooperation with EthosEnergy Italia S.p.a.. The paper presents a new design, which, starting from the original solution featuring fifteen smooth pipes, adopts an improved geometry characterized by the presence of turbulators. The activity has been carried out using Computational Fluid Dynamics (CFD) for the coolant/blade interaction and one-dimensional models developed at EthosEnergy for the redistribution of the cooling flows in the cavities. The mutual effects between the coolant fluid and the blade are analyzed using a Conjugate Heat Transfer (CHT) approach with Star-CCM+. The validation of the computational approach has been performed exploiting the experimental data available for the NASA C3X test case. The TG20 rotating blade of the first turbine row has been analyzed considering the two different coolant configurations. The impact of the main flow on the thermal field has initially been included by imposing a temperature field on the blade surface. The latter field has in turn been obtained by means of a separate computation for the solid only. Full CHT simulations has hence been performed, thus quantifying the accuracy of the proposed approach. The obtained results are discussed in terms of thermo-fluid-dynamic effects.

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.

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