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.

On-Design and Off-Design Performance Analysis of a Gas Turbine Combined Cycle Using the Exergy Method

2000 ◽  
Author(s):  
Alcides Codeceira Neto ◽  
Pericles Pilidis
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Exergy Analysis ◽  
Pressure Ratio ◽  
Calorific Value ◽  
Combined Cycle ◽  
Exergy Destruction ◽  
Turbine Engine ◽  
Design Point

The present paper describes an on-design and an off-design performance study of gas turbine combined cycle based power plants. The exergy analysis has been carried out along with the performance assessment, considering the overall plant exergetic efficiency and the exergy destruction in the various components of the plant. The exergy method highlights irreversibility within the plant components, and it is of particular interest in this investigation. A computational analysis has been carried out to investigate the effects of compressor pressure ratio and gas turbine entry temperature on the thermodynamic performance of combined gas / steam power cycles. The exergy analysis has been performed for on-design point calculations, considering single shaft gas turbines with different compressor pressure ratios and turbine entry temperatures. Nearly 100 MW shaft power gas turbine engines burning natural gas fuel have been selected in this study. The off-design calculations have been performed for one of the gas turbines selected from the on-design point studies. For this particular gas turbine engine, fuel has been changed from natural gas to a low calorific value fuel gas originated from the gasification of wood. The exergy analysis indicates that maximum exergy is destroyed in the combustor, in the case of combined gas / steam cycles burning natural gas. For these studies on-design point, the exergy destruction in the combustor is found to decrease with increasing compressor pressure ratio to an optimum value and with increasing turbine entry temperature. In the off-design case the gas turbine engine is burning low calorific value fuel originated from the gasification of wood. The maximum exergy destruction occurs in the gasification process, followed by the combustion process in the gas turbine.

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.

Design Problems of a Regenerative Turboprop Aircraft Engine

1964 ◽  
Author(s):  
R. E. Cutler ◽  
Esten W. Spears
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Reduction Gear ◽  
Operational Flexibility ◽  
Design Problems ◽  
Turbine Engine ◽  
Turbine Cooling ◽  
Engine Design ◽  
Engine Components ◽  
The Military

The military and industry have long recognized the potential of the regenerative-cycle gas turbine. Only recently has the “state-of-the-art” in regenerators and other lightweight turbine-engine components made it feasible to apply regeneration to aircraft engines. In applying regeneration to the aircraft gas turbine certain unique engine-design problems are encountered, such as: (a) Configuration and arrangement of lightweight, high effectiveness regenerator; (b) combustion system with side entry air; (c) turbine cooling at high inlet temperatures; (d) compressor operating flexibility; (e) control system for optimum engine response and operational flexibility; (f) configuration and arrangement of propeller and reduction gear.

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.

Novel Gas Turbine Exhaust Temperature Measurement System

2013 ◽  
Author(s):  
Upul DeSilva ◽  
Richard H. Bunce ◽  
Heiko Claussen
Keyword(s):  
Temperature Measurement ◽  
Gas Turbine ◽  
Speed Of Sound ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Process Gas ◽  
Exhaust Duct ◽  
Topographical Mapping ◽  
Gas Turbine Exhaust ◽  
Turbine Exhaust

Siemens Energy, Inc. has been investigating the potential of a new approach to measuring the process gas temperature leaving the turbine of their heavy industrial gas turbine engines using an acoustic pyrometer system. This system measures the bulk temperature crossing a plane behinds the last row of turbine blades and is a non-intrusive measurement. It has the potential to replace the current intrusive multiple point measurement sensor arrays for both engine control and performance evaluation. The acoustic pyrometer is a device that measures the transit time of an acoustic pulse across the exhaust duct of the engine. An estimate of the temperature of the process fluid can be made from the transit time. Multiple passes may be made at various radial positions to improve the measurement. The gas turbine exhaust is a challenging environment for acoustic temperature measurement where there can be significant temperature stratification and high velocity. Previous applications of acoustic pyrometers to measure process gas temperature in power plants have been confined to applications such as boilers where rapid temperature changes are not expected and fluid velocity patterns are well known. The present study describes the results of acoustic pyrometer testing in an operating gas turbine engine under load using an active acoustic pyrometer system containing eight sets of transmitters and receivers, all external to the turbine exhaust flow path. This active method technology is based on the temperature dependence of the isentropic speed of sound from the simple ideal gas assumptions. Sound transmitters and receivers are mounted around the exhaust duct to measure the speed of sound. Very sophisticated topographical mapping techniques have been developed to extract temperature distribution from using any where from 2 to 8 sensors with up to 24 paths and 400 points. Cross correlation of sensor results to obtain topographical mapping of gas isotherms in a plane in full engine field tests have been conducted to prove the feasible of this technology on a gas turbine engine. The initial installation of the active acoustic pyrometer system in an engine exhaust was accomplished in 2009. All the tests indicate that the steady state measurements of the acoustic pyrometer system fall within 10C of the measured exhaust thermocouple data. An additional installation on a different model engine was subsequently made and data have been gathered and analyzed. Results of these tests are presented and future evaluation options discussed.

Gas Turbine Engines Safe Life Criterion Analysis

2014 ◽  
Vol 533 ◽  
pp. 346-349
Author(s):  
Jie Hu
Keyword(s):  
Gas Turbine ◽  
Early Period ◽  
Turbine Engines ◽  
Structural Development ◽  
Development Programs ◽  
Turbine Engine ◽  
Safe Life ◽  
Engine Design ◽  
Prediction Techniques ◽  
The Military

Life concepts have evolved and improved since the early period of the gas turbine engine. Early on, passing a 150-h test was the main "pass or fail" criteria used to qualify a new engine design to enter production and service. Engine life development and life prediction techniques evolved mostly in response to durability problems, customer demands, and/or regulatory involvement. The safe life and damage tolerance concepts have been the two most widely used design methods for producing components to meet life requirements. More recently, however, the combination of both life concepts is the preferred life method for both commercial and military and is required by the military in their engine structural development programs.

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