Design of a Family of Packages for a 7500-kW Industrial Gas Turbine

1978 ◽  
Author(s):  
D. Williamson ◽  
J. Fistere
Keyword(s):  
Gas Turbine ◽  
Economic Evaluations ◽  
Successful Operation ◽  
Aerodynamic Efficiency ◽  
Turbine Engine ◽  
Reliable Monitoring ◽  
Cost Efficient ◽  
Electronic Load ◽  
Major Equipment ◽  
Industrial Gas Turbine

When a new large gas turbine engine is developed for use in economically sensitive environments, it is necessary to make careful trade-off decisions on such potentially conflicting requirements as: ruggedness versus weight, high aerodynamic efficiency versus low first cost, efficient high firing temperatures versus air quality standards and long life, etc. Similarly, the equipment to be driven by the gas turbine must also be carefully selected and developed for optimum application. In addition to the above, it is the task of the package to integrate the primary machinery and all of its supporting systems into a single cohesive, product. Therefore, similar sound technical, functional, and economic evaluations must be made for fuel, lubricating, gas sealing, control systems, and the physical arrangement of the package itself. Sound application of the fundamental concepts of reliability, redundancy, and safety are essential to the successful operation of these systems, which must meet life criteria of 30,000 hr or more of continuous operation without major maintenance. All turbine systems are automatic and are frequently called upon to operate remotely in marine, desert, and arctic environments. The ability of such systems to respond to a variety of electronic load and speed signals predictably and accurately is essential to the acceptance of the gas turbine in industrial application. Efficient, effective, and reliable monitoring systems, which will sense essential operating parameters and act to protect the major equipment from catastrophic failure, must themselves be selected for reliability, accuracy, and endurance. The combination of all of the above forms the essence of design criteria for gas turbine packages.

scholarly journals Application of a Vehicular Designed, Heavy Duty Gas Turbine Engine to a Military Generator Set

1985 ◽  
Author(s):  
Samuel C. Laux ◽  
Robert N. Ware
Keyword(s):  
Gas Turbine ◽  
Rotating Disk ◽  
Gas Turbine Engine ◽  
Successful Operation ◽  
Turbine Engine ◽  
Air Defense ◽  
Heavy Duty Gas Turbine ◽  
Generator Sets ◽  
Industrial Gas Turbine ◽  
The Military

The Patriot Air Defense Missile System (formerly SAM-D) is being deployed in Europe. The powerplant supplying electricity to the radar set and to the engagement control station is DOD Model D-424A, powered by the Allison Model GT-404 industrial gas turbine (IGT) engine. Designed as a vehicular engine, the application in a generator set is an interesting one, utilizing many of the following features originally intended to enhance the performance of trucks and buses: • Dual, rotating disk regenerators dramatically improve fuel consumption by transferring heat energy from the exhaust gas stream to compressor discharge. • Power transfer, intended to provide part load fuel economy in vehicles, is modified to furnish free-shaft start-fixed shaft run in generator sets. • Free-shaft starts allow successful operation down to −50°F without auxiliary heaters. The resultant gas turbine engine driven generator set — 150 kW, transportable, skid mounted, alternating current 400 Hz, tactical — has met the military requirements for performance and reliability.

scholarly journals Industrial Gas Turbine Engine Catalytic Pilot Combustor-Prototype Testing

2010 ◽  
Author(s):  
Shahrokh Etemad ◽  
Benjamin Baird ◽  
Sandeep Alavandi ◽  
William Pfefferle
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Industrial Gas Turbine ◽  
Prototype Testing

scholarly journals Mars™ SoLoNOx Combustion System CFD Modeling

1995 ◽  
Author(s):  
Matthew E. Thomas ◽  
Mark J. Ostrander ◽  
Andy D. Leonard ◽  
Mel Noble ◽  
Colin Etheridge
Keyword(s):  
Gas Turbine ◽  
System Development ◽  
Cfd Modeling ◽  
Cfd Analysis ◽  
Combustion System ◽  
Design Environment ◽  
Turbine Engine ◽  
Combustion Modeling ◽  
Premix Combustion ◽  
Industrial Gas Turbine

CFD analysis methods were successfully implemented and verified with ongoing industrial gas turbine engine lean premix combustion system development. Selected aspects of diffusion and lean premix combustion modeling, predictions, observations and validated CFD results associated with the Solar Turbines Mars™ SoLoNOx combustor are presented. CO and NOx emission formation modeling details applicable to parametric CFD analysis in an industrial design environment are discussed. This effort culminated in identifying phenomena and methods of potentially further reducing NOx and CO emissions while improving engine operability in the Mars™ SoLoNOx combustion system. A potential explanation for the abrupt rise in CO formation observed in many gas turbine lean premix combustion systems is presented.

Conversion of a Heavy-Duty Industrial Gas Turbine to Combined Cycle

1983 ◽  
Vol 105 (4) ◽  
pp. 870-874
Author(s):  
D. W. Leffler ◽  
B. S. Roberts
Keyword(s):  
Gas Turbine ◽  
Heavy Oil ◽  
Fuel Efficiency ◽  
Combined Cycle ◽  
Evaluation Design ◽  
Heavy Duty ◽  
Successful Operation ◽  
Combined Cycle Plant ◽  
Industrial Gas Turbine

This paper discusses the evaluation, design, and operation of a combined-cycle plant for Bahamas Electricity Corporation in Nassau, Bahamas. The plant was designed to provide maximum fuel efficiency, satisfactorily operate to 40 percent load, and includes provisions for heavy oil firing in the gas turbine. The system was started up July, 1982 and has been in successful operation since then.

Development of FT9 Marine Gas Turbine

1981 ◽  
Author(s):  
D. A. Groghan ◽  
C. L. Miller
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
System A ◽  
On Line ◽  
Condition Monitoring System ◽  
Industrial Gas Turbine ◽  
Engine Condition

The FT9 Marine Gas Turbine development program was initiated in August 1973 by the Naval Sea Systems Command to fulfill, in part, the requirement for a family of gas turbine engines ranging in power from 1000 to 30,000 hp. The FT9 satisfied the requirement to develop a 30,000 hp class marine gas turbine. The FT9 is a derivative of the Pratt & Whitney Aircraft JT9D engine, which powers Boeing 747, DC-10 and A300 aircraft, and of the FT4 industrial gas turbine engine. The FT9 specification also required development of an on-line engine condition monitoring system. A rigorous development test program showed the FT9 has met all specified U.S. Navy requirements and demonstrated its suitability for use in U.S. Navy combatant ships.

Performance Deterioration in Industrial Gas Turbines

1992 ◽  
Vol 114 (2) ◽  
pp. 161-168 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

scholarly journals Assessing Exergy-Based Economic and Sustainability Analyses of a Military Gas Turbine Engine Fueled with Various Fuels

Energies ◽  
2020 ◽  
Vol 13 (15) ◽  
pp. 3823
Author(s):  
Burak Yuksel ◽  
Huseyin Gunerhan ◽  
Arif Hepbasli
Keyword(s):  
Gas Turbine ◽  
Exergy Destruction ◽  
Fuel Utilization ◽  
Cost Index ◽  
Cost Analyses ◽  
Turbine Engine ◽  
Exhaust Duct ◽  
Cost Efficient ◽  
The Military ◽  
Process Mode

This research put forth exergy-based economic and sustainability analyses of a (J85-GE-5H) military turbojet engine (TJE). Firstly, sustainability, conventional exergoeconomic and advanced exergoeconomic cost analyses were executed utilizing kerosene fuel according to real engine working circumstances. The engine was likewise investigated parametrically, considering H2 fuel utilization. The sustainable economic analysis assessment of the TJE was finally actualized by comparing the acquired outcomes for both fuels. The entire engine’s unit exergy cost of product (cPr) with kerosene was determined 76.45 $/GJ for the military (MIL) process mode (PM), whereas it was computed 94.97 $/GJ for the afterburner (AB) PM. Given the use of H2, the cPr increased to 179 and 288 $/GJ for the aforementioned two modes, seriatim. While the sustainability cost index (SCI) values were obtained 52.86 and 78.84 $/GJ for the MIL and AB PM, seriatim, they became 128 and 244 $/GJ when considering H2. Consequently, the higher exergy demolitions occurring in the afterburner exhaust duct (ABED) and combustion chamber (CC) sections led to higher exergy destruction costs in the TJE. However, the engine worked less cost efficient with H2 fuel rather than JP-8 fuel because of the higher cost value of fuel.

Performance Deterioration in Industrial Gas Turbines

1991 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

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