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contributor authorStefano Campanari
contributor authorUwe Wollrab
contributor authorGiampaolo Manzolini
contributor authorAndrea Beretti
date accessioned2017-05-09T00:28:00Z
date available2017-05-09T00:28:00Z
date copyrightMarch, 2008
date issued2008
identifier issn1528-8919
identifier otherJETPEZ-27001#021701_1.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/137973
description abstractIn recent years, civil aircraft projects are showing a continuous increase in the demand of onboard electrical power, both for the partial substitution of hydraulic or pneumatic controls and drives with electrical ones, and for the consumption of new auxiliary systems developed in response to flight safety and environmental control issues. Aiming to generate onboard power with low emissions and better efficiency, several manufacturers and research groups are considering the possibility to produce a relevant fraction of the electrical power required by the aircraft by a fuel cell system. The first step would be to replace the conventional auxiliary power unit (based on a small gas turbine) with a polymer electrolyte membrane (PEM) fuel cell type, which today is favored with respect to other fuel cell types; thanks to its higher power density and faster startup. The PEM fuel cell can be fed with a hydrogen rich gas coming from a fuel reformer, operating with the same jet fuel used by the aircraft, or relying on a dedicated hydrogen storage onboard. The cell requires also an air compression unit, where the temperature, pressure, and humidity of the air stream feeding the PEM unit during land and in-flight operation strongly influence the performance and the physical integrity of the fuel cell. In this work we consider different system architectures, where the air compression system may exploit an electrically driven compressor or a turbocharger unit. The compressor type and the system pressure level are optimized according to a fuel cell simulation model, which calculates the cell voltage and efficiency as a function of temperature and pressure, calibrated over the performances of real PEM cell components. The system performances are discussed under different operating conditions, covering ground operation, and intermediate and high altitude cruise conditions. The optimized configuration is selected, presenting energy balances and a complete thermodynamic analysis.
publisherThe American Society of Mechanical Engineers (ASME)
titlePerformance Assessment of Turbocharged Pem Fuel Cell Systems for Civil Aircraft Onboard Power Production
typeJournal Paper
journal volume130
journal issue2
journal titleJournal of Engineering for Gas Turbines and Power
identifier doi10.1115/1.2772636
journal fristpage21701
identifier eissn0742-4795
keywordsPressure
keywordsTemperature
keywordsFuels
keywordsCompressors
keywordsFuel cells
keywordsAircraft
keywordsHydrogen
keywordsProton exchange membrane fuel cells
keywordsProton exchange membranes
keywordsElectric potential
keywordsFlight
keywordsElectricity (Physics)
keywordsTurbines
keywordsFlow (Dynamics)
keywordsCompression
keywordsIndustrial plants AND Emissions
treeJournal of Engineering for Gas Turbines and Power:;2008:;volume( 130 ):;issue: 002
contenttypeFulltext


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