Development of the 5MW Power Generation Gas Turbine Engine

2011 ◽  
Author(s):  
Sooyong Kim ◽  
Sungryong Lee ◽  
Jewook Ryu ◽  
V. E. Spitsyn
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Nuclear Power ◽  
Peak Load ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Load Power ◽  
The Future ◽  
Lng Fuel ◽  
Base Load

Gas turbine engine has been applied to the aircraft and ship propulsion with its advantages of compactness and comparatively short starting time. With a significant improvement in gas turbine efficiency with development of super alloy materials and advancement in cooling technologies in the second half of 1990s, its importance as a source of base load as well as peak load power generation has been increasing. However, with increased demand in nuclear power and renewable energy in the 21st century, there seems to be speculations among the power generation industries that gas turbine will take more or less a buffering role supplementing the irregular inflow of electricity to the grid rather than acting as a base load power source. With the shift in the role of gas turbine from base to supplementary, CHP application based on small powered gas turbine utilizing biogas or syngas as its fuel is expected to increase in the future. In this context, this paper describes the development result of 5MW gas turbine engine for CHP application. It can be operated with LNG or syngas of low LHV fuel. Originally, the engine was designed for LNG as its primary fuel, but since the importance of syngas power generation market will be increasing in the future, a complementary work for modification of combustor part has been carried out and has been tested. However, this paper deals with the parts developed with the use of LNG fuel. The test result of emission characteristics meets the standards required in Korea. The development has been made through the cooperation of Doosan Heavy Industry (DHI, Korea) and Zory-Mashproekt (Ukraine).

scholarly journals The Prototype of a 100-Mw, 3000 Rpm Gas Turbine Series for Power Generation

1974 ◽  
Author(s):  
G. P. Frigieri
Keyword(s):  
Power Generation ◽  
Control System ◽  
Gas Turbine ◽  
Peak Load ◽  
Gas Turbine Engine ◽  
Advanced Stage ◽  
Design Features ◽  
Test Program ◽  
Turbine Engine ◽  
Prototype Test

This paper presents the prototype of a large gas turbine new series whose peculiar characteristics make the same very attractive for both base and peak load applications. The gas turbine engine, now in an advanced stage of manufacturing, is scheduled to be bench tested in the last quarter of the year. The major design features of the gas turbine engine together with the prototype test program are described. In addition, the peculiar characteristics of the control system and and package installation are mentioned.

The Potential Impact of Future Fuels on Small Gas Turbine Engines

1982 ◽  
Author(s):  
J. A. Saintsbury ◽  
P. Sampath
Keyword(s):  
Gas Turbine ◽  
Operating Experience ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
The Future ◽  
Potential Impact ◽  
The Impact ◽  
Whitney Aircraft

The impact of potential aviation gas turbine fuels available in the near to midterm, is reviewed with particular reference to the small aviation gas turbine engine. The future course of gas turbine combustion R&D, and the probable need for compromise in fuels and engine technology, is also discussed. Operating experience to date on Pratt & Whitney Aircraft of Canada PT6 engines, with fuels not currently considered of aviation quality, is reported.

Development of the Ceramic Gas Turbine Engine System (CGT301)

1999 ◽  
Author(s):  
Takeshi Sakida ◽  
Shinya Tanaka ◽  
Takao Mikami ◽  
Masashi Tatsuzawa ◽  
Tomoki Taoka
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
The Future ◽  
Engine System ◽  
Primary Type ◽  
Three Phases

The CGT301 ceramic gas turbine has been developed under a contract from NEDO as a part of the New Sunshine Program of MITI since 1988 to 1998. The CGT301 is a recuperated, single-shaft ceramic gas turbine. Ceramic parts are used in the hot section of the engine, such as turbine blades, nozzle vanes, combustion liners and so on. As a primary feature of this turbine, the rotors are composed of ceramic blades inserted into metallic disks (“hybrid rotor”) for the future applicability to the large gas turbine. The R & D program consists of three phases, the model metal gas turbine, the primary type ceramic gas turbine and the pilot ceramic gas turbine. The pilot ceramic gas turbine showed etable operation at TIT of 1,350°C. This paper presents the progress in the development of the pilot ceramic gas turbine of CGT301.

Lycoming T-53 Gas Turbine Engine Modification for Industrial Application

2007 ◽  
Author(s):  
Vladimir Lupandin ◽  
Martyn Hexter ◽  
Alexander Nikolayev
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Alternative Fuels ◽  
Phase 1 ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Combustion System ◽  
Original Design ◽  
High Hydrogen ◽  
Turbine Engine

This paper describes a development program active at Magellan Aerospace Corporation since 2003, whereby specific modifications are incorporated into an Avco Lycoming T-53 helicopter gas turbine engine to enable it to function as a ground based Industrial unit for distributed power generation. The Lycoming T-53 is a very well proven and reliable two shaft gas turbine engine whose design can be traced back to the 1950s and the fact of its continued service to the present day is a tribute to the original design/development team. Phase 1 of the Program introduces abradable rotor path linings, blade coatings and changes to seal and blade tip clearances. Magellan has built a test cell to run the power generation units to full speed and full power in compliance with ISO 2314. In co-operation with Zorya-Mashproekt, Ukraine, the exhaust emissions of the existing combustion system for natural gas was reduced by 30%. New nozzles for low heat value fuels and for high hydrogen content fuels (up to 60% H2) have been developed. The T-53 gas turbine engine exhaust gas temperature is typically around 620 deg C, which makes it a very good candidate for co-generation and recuperated applications. As per Phase 2 of the program, the existing helicopter integral gearbox and separate industrial step-down gearbox will be replaced with single integral gearbox that will use the same lubrication oil system as the gas turbine engine. The engine power output will increase to 1200 kW at the generator terminals with an improvement to 25% efficiency ISO. Phase 3 of the Program will see the introduction of a new silo type combustion system, developed in order to utilize alternative fuels such as bio-diesel, biofuel (product of wood pyrolysis), land fill gases, syn gases etc. Phase 4 of the Program in cooperation with ORMA, Russia will introduce a recuperator into the package and is expected to realize a boost in overall efficiency to 37%. The results of testing the first two T-53 industrial gas turbine engines modified per Phase 1 will be presented.

Thermodynamic Equillibrium Model of Emission Levels of Small Gas Turbine Engine Using Kerosene Ethanol Blends

2006 ◽  
Author(s):  
Hitesh K. Solanki ◽  
S. A. Channiwala
Keyword(s):  
Gas Turbine ◽  
Peak Load ◽  
Equilibrium Temperature ◽  
Gas Turbine Engine ◽  
Liquid Fuels ◽  
Turbine Engine ◽  
Oxygenated Fuel ◽  
Ethanol Addition ◽  
Basic Objective ◽  
Ethanol Blends

The increasing awareness towards environment protection and peak load response is accredited in the development of gas turbine system. Many such system preliminary utilizes liquid fuels like kerosene. The emission level with such liquid fuel may be reduced by addition of oxygenated fuel like ethanol. Hence, the basic objective of present paper is to investigate analytically the influence of ethanol addition on emission levels of the kerosene fired small laboratory gas turbine unit. This paper discusses about the theoretical investigation on emission levels with kerosene-ethanol blended fuel using thermodynamic equilibrium model. The theoretical investigations have been carried out on Gilkes GT 85/2 twin shaft Gas Turbine Engine with ethanol blended kerosene fuel to a concentration level of 25% ethanol in the step of 5% increment. The investigations of the emission levels were carried out for CO2, CO, O2, H2, N2, H2O, OH and NO with respect to equilibrium temperature at different overall equivalence ratios ranging from 0.1 to 1.1. It is worth to mention that the equilibrium thermodynamic model clearly indicates that in narrow operative range of equivalence ratio (0.1 to 0.2) and the ethanol addition to an extent of 10% to 15% clearly offers reduced emission levels.

Development of Small-sized Gas Turbine Engine Control System for Power Generation

2011 ◽  
Vol 14 (4) ◽  
pp. 52-56
Author(s):  
Seong-Jin Hong ◽  
Seung-Min Kim ◽  
Sim-Kyun Yook ◽  
Sam-Sik Nam
Keyword(s):  
Power Generation ◽  
Control System ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Turbine Engine ◽  
Engine Control System

scholarly journals Total Turbine Energy in Refrigeration Cycles

1964 ◽  
Author(s):  
S. T. Robinson ◽  
J. W. Glessner
Keyword(s):  
Power Generation ◽  
Total Energy ◽  
Electric Power ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Absorption Refrigeration ◽  
Electric Power Generation ◽  
Turbine Engine ◽  
Heating And Cooling

The means of using total energy from a gas-turbine engine in various refrigeration systems are reviewed. Combinations of heating and cooling or electric power generation and cooling are discussed as well as combined centrifugal and absorption refrigeration systems. The economics of gas-burning turbine engines are investigated and shown to be attractive in these applications.

Optimization of 200 to 3000 W Gas Turbine MEMS Arrangement

2009 ◽  
Author(s):  
A. V. Sudarev ◽  
A. A. Suryaninov ◽  
B. A. Bazarov ◽  
V. S. Ten ◽  
L. Lelait ◽  
...  
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Power Efficiency ◽  
High Speed ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Specific Power ◽  
Environmental Friendliness ◽  
Turbine Engine ◽  
Electric Generator

The persistent increase in demand for compact efficient power generation plants for the decentralized power supply systems applications, pipelines, micro air vehicles, electronics, etc stipulates developments of independent micro sources. Application of the micro gas turbine engine (μGTE) as an electric generator drive allows a sharp increase in the specific energy and operation independence, elimination of ambient temperature effects on the specific power, environmental friendliness improvement. However, GTE miniaturization causes its efficiency decreasing. Hence, there is a need in improvement of the micro engine of 200–3,000W power efficiency. The approach proposed is the ceramic tunnel turbomachine concept for the regenerative μGTE (MEMS-based) application [1, 2, 3] with conventional annular systems of vanes replaced with three-dimensional conic channels. The μGTE turbocompressor unit design is dependent on the conceptual arrangement approach i.e. a manner the gas turbine engine micro turbocompressor (μTC) is joined with the driven micro electric generator (μEG) assumes a great importance. Two conceptually opposite μTC concepts over the turbocompressor unit are considered: - the μTC rotor connected with the μEG rotor by an electromagnet coupling; - appropriate elements of μEG built into the rotor and stator sections of μTC. Examination of the essentially different concepts of the μEG - micro turbocompressor (μTC) arrangement demonstrated that an independent power generation, high temperature, and high speed μGTE reliable operating can be ensured by different arrangements, e.g. with the rotor and stator sections of the electric generator placed between the appropriate turbine and compressor stage devices. In this case it is easier, compared to some other approaches, to evade an unpropitious effect on the μTC rotor strength characteristics (total stress level, critical velocities within the speed operation range, radial and axial deformations, etc) imposed by sizes and mass of the contact-free electromagnet couplings elements. This inference ensues, also, from the studies conducted [4, 5].

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