Method for the Preliminary Design of the Fan Propulsion System
Identifikátory výsledku
Kód výsledku v IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F17%3A00320635" target="_blank" >RIV/68407700:21220/17:00320635 - isvavai.cz</a>
Výsledek na webu
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DOI - Digital Object Identifier
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Alternativní jazyky
Jazyk výsledku
angličtina
Název v původním jazyce
Method for the Preliminary Design of the Fan Propulsion System
Popis výsledku v původním jazyce
UL-39 ultralight aircraft has been developed at the Department of Aerospace Engineering, Czech Technical University in Prague. This aircraft is powered by unique propulsion system, which consists of a fan driven by piston engine. Design and optimization methods for single components are available in various textbooks, papers and reference works. However, unknown input parameters are required for the design of any of these components. Experience from the turbofan engines cannot be directly used due to the different characteristics of piston engine. This paper presents method for the computation of these input parameters. It is shown that almost constant fan power consumption at constant engine RPM can be reached for the speed range from 0 to maximum flight velocity, which means optimal usage of engine power.
Název v anglickém jazyce
Method for the Preliminary Design of the Fan Propulsion System
Popis výsledku anglicky
UL-39 ultralight aircraft has been developed at the Department of Aerospace Engineering, Czech Technical University in Prague. This aircraft is powered by unique propulsion system, which consists of a fan driven by piston engine. Design and optimization methods for single components are available in various textbooks, papers and reference works. However, unknown input parameters are required for the design of any of these components. Experience from the turbofan engines cannot be directly used due to the different characteristics of piston engine. This paper presents method for the computation of these input parameters. It is shown that almost constant fan power consumption at constant engine RPM can be reached for the speed range from 0 to maximum flight velocity, which means optimal usage of engine power.
Klasifikace
Druh
O - Ostatní výsledky
CEP obor
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OECD FORD obor
20304 - Aerospace engineering
Návaznosti výsledku
Projekt
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Návaznosti
S - Specificky vyzkum na vysokych skolach
Ostatní
Rok uplatnění
2017
Kód důvěrnosti údajů
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů