scholarly journals Performance analysis of grid-connected micro-cogeneration system based on the internal combustion engine

2019 ◽  
Vol 3 (4) ◽  
pp. 164-169
Author(s):  
Abdurrahman Yavuzdeğer ◽  
Fırat Ekinci
Keyword(s):  
Performance Analysis ◽  
Internal Combustion Engine ◽  
Combustion Engine ◽  
Internal Combustion ◽  
Cogeneration System

Design of Turbo-Compression System for HALE UAV Propulsion System

2018 ◽  
Author(s):  
Young Seok Kang ◽  
Dong Ho Rhee ◽  
Byeung Jun Lim ◽  
Sangook Jun ◽  
Tae Choon Park ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Performance Analysis ◽  
Internal Combustion Engine ◽  
High Altitude ◽  
Combustion Engine ◽  
Internal Combustion ◽  
Propulsion System ◽  
Flight Altitude ◽  
Compression System ◽  
Main Components

A turbo-compression system design and its performance analysis procedure for a high altitude long endurance UAV (HALE UAV), of which cruising altitude is within the stratosphere, is presented. To fly at a relatively low speed for a long time and to make engine performance less sensitive to flight altitude, a hydrogen fueled internal combustion engine was chosen for a propulsion system. To utilize an internal combustion engine as a propulsion system at a high altitude, a proper inlet pressure boost system such as a series of turbochargers is required. Hydrogen is highly reactive gas and sometimes backfiring or preignition may occur due to its low ignition energy at stoichiometric ratio. Therefore, fuel to air ratio should be reduced as low as 0.6 to avoid such phenomena. Then rarefied ambient intake air pressure should be boosted up to 1.7 bar to produce required power from the lean burn engine. To gain high pressure ratio from the turbo compression system, at least three stage serial turbocharger with proper intercooler system at each compressor exhaust is required. To analyze multi-stage turbocharger performance at the cruising altitude, an explicit one-dimensional analysis method has been established mainly by matching required power between compressors and turbines. Each compressor performances were corrected according to Reynolds number at a given flight altitude. Compressor efficiency and surge margin deteriorate as the operating altitude increases. Then compressor efficiencies were reflected as functions of flight altitude and corresponding Reynolds number. Once operating points of each turbocharger was determined, then adequate turbochargers were searched for from commercially available models based on performance analysis results. Also, adequate water to air intercoolers were chosen for the turbo-compression system to secure flexibility of placing main components inside the engine bay as well as to obtain high heat exchange efficiency of the heat exchangers. Based on the designed turbo-compression system, technical demonstration test of the turbo-compression system inside altitude environment test chamber in Korea Aerospace Research Institute is planned. Altitude condition in stratosphere is simulated mainly with two stage centrifugal compressor and additional fan will be used to fine control the flight altitude. The turbo compression system will be controlled with a single waste gate located just downstream of the engine to secure simple controllability of the turbo compression system. The test results will validate main components as well as system layout design methods and give more reliable control schedule of the turbo compressions system according to the flight altitude.

Energetic, Exergetic and Exergetic Cost Analysis for a Cogeneration System Integrated by an Internal Combustion Engine, HRSG and an Absorption Refrigeration System

Volume 1 ◽  
2004 ◽  
Author(s):  
Raul Gonzalez Palomina ◽  
Silvia A. Nebra
Keyword(s):  
Cost Analysis ◽  
Internal Combustion Engine ◽  
Combustion Engine ◽  
Internal Combustion ◽  
System Component ◽  
Total System ◽  
Absorption Refrigeration ◽  
Refrigeration System ◽  
Cogeneration System ◽  
Absorption Refrigeration System

The objective of this work is to do an energetic, exergetic and thermoeconomic analysis of a cogeneration system. This system is composed of an internal combustion engine, a heat recovery steam generator (HRSG), an absorption refrigeration system (ARS) and a cooling tower (CT). With the use of the mass and energy balances, several parameters of efficiency based in the First Law of Thermodynamics were calculated for the cogeneration system. With the use of the exergy balance, the exergetic efficiencies for the engine, HRSG, ARS, CT and the total system were calculated. Also, the irreversibility contribution of each system component was shown. An optimization was done, having as functional objective the maximization of the difference of the operational incomes and expenses. An exergetic cost analysis was made using the Theory of the Cost Exergetic (TCE). The system in study gets to save up to 28,5% of fuel in comparison with the divided production of heat and electric energy. The largest irreversibility that happened in the cycle is due to the engine, which participates in the average with 78% of the total. The analysis with the TCE showed that the product of the ARS is more expensive in comparison with the process heat and electricity.

scholarly journals Performance Analysis of an Internal Combustion Engine Using Butanol as an additive in Ethanol Gasoline Blended Fuel

2018 ◽  
Vol 09 (01) ◽  
pp. 1-8
Author(s):  
SYED NABEEL JAMAL BARI ◽  
◽  
D.C. VISHVAKARMA ◽  
AKHLESH KUMAR SHAKYA ◽  
◽  
...  
Keyword(s):  
Performance Analysis ◽  
Internal Combustion Engine ◽  
Combustion Engine ◽  
Internal Combustion ◽  
Blended Fuel
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