Experience With Mobile Gas Turbines

1963 ◽  
Author(s):  
R. Artigas ◽  
E. Bernhardt
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
The Third ◽  
Made In

The Comision Federal de Electricidad of Mexico in 1954 ordered two mobile gas-turbine sets; an additional identical set was ordered in 1955. The first two units went into service in 1955 and the third in 1956. Therefore, all three units have been operated for more than 6 years. This paper reviews briefly the operation data and the difficulties and problems involved. Finally, a few remarks are made in relation to future use of similar units.

scholarly journals Breaking the Barriers

2012 ◽  
Vol 134 (05) ◽  
pp. 32-37
Author(s):  
Lee S. Langston
Keyword(s):  
Fluid Mechanics ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Solid Mechanics ◽  
Commercial Aircraft ◽  
Commercial Aviation ◽  
New Developments ◽  
Exhaust Heat ◽  
Turbine Component ◽  
Made In

This article explores the new developments in the field of gas turbines and the recent progress that has been made in the industry. The gas turbine industry has had its ups and downs over the past 20 years, but the production of engines for commercial aircraft has become the source for most of its growth of late. Pratt & Whitney’s recent introduction of its new geared turbofan engine is an example of the primacy of engine technology in aviation. Many advances in commercial aviation gas turbine technology are first developed under military contracts, since jet fighters push their engines to the limit. Distributed generation and cogeneration, where the exhaust heat is used directly, are other frontiers for gas turbines. Work in fluid mechanics, heat transfer, and solid mechanics has led to continued advances in compressor and turbine component performance and life. In addition, gas turbine combustion is constantly being improved through chemical and fluid mechanics research.

Brush Seals for the No. 3 Bearing of a Model 7EA Gas Turbine

2000 ◽  
Author(s):  
Steve Ingistov ◽  
Gary Meredith ◽  
Erik Sulda
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Elevated Temperatures ◽  
Axial Compressor ◽  
Lubricating Oil ◽  
Additional Element ◽  
The Third ◽  
Air Stream ◽  
Brush Seals

Gas Turbines in power generation are frequently of the single rotor type. The rotor is directly connected to the electrical generator. The rotor may be supported by two journal bearings or in some cases there is an additional journal bearing situated between the axial compressor discharge and the gas turbine intake. This third bearing serves to provide the rotor with additional support required to reduce rotor dynamic instabilities. The third bearing is, therefore, inside the machine housing and a significant amount of maintenance work is necessary to inspect it. The third bearing is also exposed to elevated temperatures by, essentially, being surrounded by compressor discharge air. A certain amount of compressor discharge air leaks through the seals into the cylindrical space around the third bearing housing and from there, due to significant pressure gradients, into the third bearing. Labyrinth seals are provided to impede air leakage from the pressurized cylindrical space into the bearing cavity. The air that leaks into the bearing housing mixes with a buffer air stream. This buffer air stream serves to cool the bearing cavity and to prevent leakage of hot, high-pressure air into the bearing cavity. Two dry air streams are then routed into the atmosphere via the coaxial space formed by two cylindrical surfaces. The portion of the buffer air stream contacting the bearing lubricating oil is de-misted in a special de-mister vessel. The de-misted air is exhausted into the atmosphere and the separated oil is returned to the gas turbine lubricating oil reservoir. This Paper discusses the introduction of brush seals into the No. 3 bearing housing as an additional element in retarding the high pressure, high temperature air infiltration into the No. 3 bearing housing.

Gas Turbines For Helicopters

1958 ◽  
Vol 62 (573) ◽  
pp. 646-654 ◽  
Author(s):  
A. W. Morley
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Liquid Fuel ◽  
Korean War ◽  
Turbine Engines ◽  
Gradual Improvement ◽  
Turbine Engine ◽  
Civil Aircraft ◽  
The Korean War ◽  
Made In

Rapid developments in the use of the helicopter were made in the Korean War. These were taking place at the time when there was considerable urge to introduce the gas turbine engine into the civil aircraft market. It was also a time when much effort was being expended on various forms of reaction propulsion, mostly for missiles. A number of new helicopter projects were started, taking advantage of the new knowledge in propulsion engineering; some utilised new gas turbine designs and others various forms of tip jet reaction. Liquid fuel rockets, ram-jets, pulse-jets and air pressure jets were tried. However, the main line of development continued to be the gradual improvement of direct mechanical drive.Since Korea the natural trend has been first to convert existing helicopters to turbine engines. When new helicopters were designed wisdom dictated mechanical drive pending the gathering of sufficient experience with other forms of rotor power, and so far the accumulated knowledge of the mechanical drive has proved of greater value to helicopter progress than the potential advantages offered by the alternative engine forms.

Thermo-Fluid Modelling for Gas Turbines—Part I: Theoretical Foundation and Uncertainty Analysis

2009 ◽  
Author(s):  
Konstantinos G. Kyprianidis ◽  
Vishal Sethi ◽  
Stephen O. T. Ogaji ◽  
Pericles Pilidis ◽  
Riti Singh ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Simulation Software ◽  
System Level ◽  
Fluid Models ◽  
Performance Simulation ◽  
Turbine Performance ◽  
Aircraft System ◽  
The Impact ◽  
Made In

In this two-part publication, various aspects of thermo-fluid modelling for gas turbines are described and their impact on performance calculations and emissions predictions at aircraft system level is assessed. Accurate and reliable fluid modelling is essential for any gas turbine performance simulation software as it provides a robust foundation for building advanced multi-disciplinary modelling capabilities. Caloric properties for generic and semi-generic gas turbine performance simulation codes can be calculated at various levels of fidelity; selection of the fidelity level is dependent upon the objectives of the simulation and execution time constraints. However, rigorous fluid modelling may not necessarily improve performance simulation accuracy unless all modelling assumptions and sources of uncertainty are aligned to the same level. Certain modelling aspects such as the introduction of chemical kinetics, and dissociation effects, may reduce computational speed and this is of significant importance for radical space exploration and novel propulsion cycle assessment. This paper describes and compares fluid models, based on different levels of fidelity, which have been developed for an industry standard gas turbine performance simulation code and an environmental assessment tool for novel propulsion cycles. The latter comprises the following modules: engine performance, aircraft performance, emissions prediction, and environmental impact. The work presented aims to fill the current literature gap by: (i) investigating the common assumptions made in thermo-fluid modelling for gas turbines and their effect on caloric properties and (ii) assessing the impact of uncertainties on performance calculations and emissions predictions at aircraft system level. In Part I of this two-part publication, a comprehensive analysis of thermo-fluid modelling for gas turbines is presented and the fluid models developed are discussed in detail. Common technical models, used for calculating caloric properties, are compared while typical assumptions made in fluid modelling, and the uncertainties induced, are examined. Several analyses, which demonstrate the effects of composition, temperature and pressure on caloric properties of working mediums for gas turbines, are presented. The working mediums examined include dry air and combustion products for various fuels and H/C ratios. The errors induced by ignoring dissociation effects are also discussed.

Reheat for Gas Turbines

1955 ◽  
Vol 59 (530) ◽  
pp. 127-150 ◽  
Author(s):  
J. L. Edwards
Keyword(s):  
United States ◽  
Great Britain ◽  
Gas Turbine ◽  
Gas Turbines ◽  
The United States ◽  
Preliminary Information ◽  
The Subject ◽  
Made In

Some five years ago the author was privileged to deliver a Section Lecture to the Royal Aeronautical Society on the subject of reheat. The present paper attempts to summarise the problems which now arise and to give some idea of the progress which has been made in the intervening years.In 1949, reheat was in its infancy in Great Britain. A certain amount of progress had been made in the United States but the information from that source was scanty and vague. Tests at the National Gas Turbine Establishment (N.G.T.E.) had given some engine data but this was in the nature of preliminary information only and was by no means complete. In fact the majority of the problems which now beset us were then completely unknown or were considered unimportant. The N.G.T.E. work was valuable, however, in that it demonstrated the practicability of reheat, although at the time the comments of many who saw this and other schemes in operation were somewhat sceptical and definitely unflattering.

scholarly journals The Coal-Fired Gas Turbine Locomotive: A New Look

1983 ◽  
Author(s):  
S. G. Liddle ◽  
B. B. Bonzo ◽  
G. P. Purohit
Keyword(s):  
Gas Turbine ◽  
Coal Combustion ◽  
Gas Turbines ◽  
Closed Cycle ◽  
Diesel Locomotive ◽  
Coal Gasifier ◽  
Open Cycle ◽  
External Combustion ◽  
Made In ◽  
New Look

The idea of a coal-fired gas turbine locomotive dates back over a half century with significant developments being made in the decade between 1944 and 1955. These developments did not lead to a locomotive which could compete with the Diesel locomotive. Today, with the increase in the price of Diesel fuel, a new look at coal-fired gas turbines is appropriate. Advances in turbomachinery technology and new means of coal combustion may have made it possible to develop a competitive locomotive. Of the various combinations of combustors, cycles, and turbines, the external combustion, closed cycle regenerative gas turbine with a fluidized bed coal combustor appears to be the best suited to this application. The external combustion, open cycle regenerative gas turbine; and the internal combustion, open cycle regenerative gas turbine with a coal gasifier are the second and third choices.

Techno-Economic Analysis and Comparative Evaluation of the Use of Gas Turbines and Reciprocating Engines in Small Scale Applications of Industrial Cogeneration

2007 ◽  
Author(s):  
Livia Arcioni ◽  
Alessandro Corradetti ◽  
Umberto Desideri ◽  
Stefania Proietti ◽  
Paolo Pogliano ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Analytical Study ◽  
Combustion Engine ◽  
Electrical Power ◽  
Payback Period ◽  
Economic Feasibility ◽  
Small Scale ◽  
Simplified Approach ◽  
Made In

This paper presents the results of a research made by University of Perugia in collaboration with Energia Spa (now Sorgenia Spa). Various analysis have been carried out to determine the techno-economic feasibility of industrial CHP plants. Due to the particular field of application, the installation of a gas turbine has been considered and compared to the traditional internal combustion engine (ICE), both being characterized by an electrical power lower than 2 MW. The feasibility study has been made in two different way: an analytical study and a simplified approach elaborated to have a first approach formula for the installation of CHP Plant. The results confirmed that IC is more convenient, giving lower payback period for the investment for this typology of installation. We present also the sensitivity analysis to determine the minimum value over that the installation of gas turbine can become convenient.

An Investigation of Component Deterioration in Gas Turbines Using Transient Performance Simulation

1988 ◽  
Author(s):  
Maurice F. White
Keyword(s):  
Gas Turbine ◽  
Mass Flow ◽  
Gas Turbines ◽  
Combustion Efficiency ◽  
Transient Performance ◽  
Performance Simulation ◽  
Turbine Plant ◽  
Physical Volume ◽  
Gas Turbine Plant ◽  
Made In

This paper discusses a program which has been developed for the prediction of steady state and transient performance of a gas turbine driven generator. The gas turbine plant was modelled using the component model principle and is based on the method for continuity of mass flow. The model requires the use of compressor and turbine characteristics together with curves for combustion efficiency. A number of simplifications are made in connecion with transient calculations. The influence of the machines physical volume on continuity of mass flow and effects of heat transfer between the gas and structural components are neglected. The model was used to investigate how component deterioration affects the important condition parameters during load transients and during rapid acceleration or deceleration. Fault conditions were simulated by manipulating the various efficiencies and loss factors for the different components in the machine. Many of the condition parameters that were investigated showed changes during acceleration which were considerably different from comparable changes in a fault free gas turbine.

KERCH STRAIT IN KAMYSH-BURUN SPIT AREA: HIGH-RESOLUTION SEISMOACOUSTIC APPROACH

2018 ◽  
Author(s):  
В. Зинько ◽  
V. Zin'ko ◽  
А. Зверев ◽  
A. Zverev ◽  
М. Федин ◽  
...  
Keyword(s):  
High Resolution ◽  
Fracture Zone ◽  
Sedimentary Cover ◽  
Sedimentary Rocks ◽  
The West ◽  
Early Generation ◽  
The Third ◽  
Azov Sea ◽  
Kerch Strait ◽  
Made In

The seismoacoustical investigations was made in the western part of the Kerch strait (Azov sea) near Kamysh-Burun spit. The fracture zone with dislocated sedimentary rocks layers and buried erosional surface was revealed to the west of spit. Three seismofacial units was revealed to the east of spit. The first unit was modern sedimentary cover. The second ones has cross-bedding features and was, probably, the part of early generation of Kamysh-Burun spit, which lied to the east of its modern position. The lower border of the second unit is the erosional surface supposed of phanagorian age. The third unit is screened by acoustic shedows in large part.

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