F. Falchetti, P. Thouraud

The reduction of weight, complexity and manufacturing costs is a major aim when designing modern turbojet engines , which leads to reduce the number of compressor stages and to increase stage loadings and efficiency. Such improvements of compressor performance, together with significant reduction of developpement times, have been obtained at SNECMA through the extensive use of advanced aerodynamic computation methods. A wide range of methods is used, from the definition of airfoils in quasi threedimensional flow to the analysis of 3D Inviscid or viscous flow for design and off-design operating blades. This paper will discuss the SNECMA aerodynamic design methodology for advanced core compressors. Special emphasis is focused on the use of advanced computation methods, such as secondary flow prediction in multistage environment , inverse design of transonic airfoils and 3D Euler or quasi-3D Navier-Stokes blade-to-blade computation.

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.113-121; 1990; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

Bestellbar

1990