M. Lecht

A flexible thermodynamical model of a bypass fan engine has been set up using constant gas properties in a first step approach investigating various core engine cycle configurations such as intercooling, recuperating and reheating. Taking a todays fan engine design as a reference and increasing the bypass ratio substantially as well as additionally modifying the thermodynamical cycle the influence on specific fuel consumption at optimal design conditions in flight is pointed out. The comparison of the different engine cycle configuations is made by considering an equal overall thrust. It has been found that an ultra high bypass concept having compressor intercooling and heat recovery might be optimal from a thermodynamical point of view. Moreover it was tried to assess the impact of the various cycles on the relative emission of NO depending on the combuster inlet conditiofls. From this all core engine cycle modifications - except the normal Joule (Brayton) cycle and the reheat cycle - reveal a potential of reduction. Neither complexity of engine design nor impact on engine weight have beeh looked at so far.

Eurpean Propulsion Forum, 1990, Köln

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1990, 1990-01, Eurpean Propulsion Forum: Future Civil Engines and the Protection of the Atmosphere - Proceedings; S.77-85; 1990; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

Bestellbar

1990