Ein inverses Verfahren zum aerodynamischen Entwurf von Triebwerksgondeln
Germany
Computer modelling operational performances of gas-turbine engines / Gazturbinu dzineju ekspluatacijas raksturliknu dato...
In the given paper mathematical description methods of operational characteristics of gas-turbine engines of various schemes were researched for application into onboard computers, simulators and test beds. The adaptive mathematical models of direct calculation of operational characteristics for gas-turbine engines of various schemes were offered a...
Gazturbinu dzineju ekspluatacijas raksturliknu datormodelesana
Latvia
Implizite Zeitintegration fuer die Simulation von Turbomaschinenstroemungen
Germany
Gazturbinu dzineju ekspluatacijas raksturliknu datormodelesana
Latvia
Gazturbinu dzineju ekspluatacijas raksturliknu datormodelesana
Latvia
Implicit time integration schemes for the simulation of turbomachinery flows / Implizite Zeitintegration fuer die Simula...
The present work is devoted to the development of an implicit time marching algorithm for the simulation of stationary and time dependent turbomachinery flows. The new implicit method allows a massive reduction of computational cost compared with conventional methods. Additionally the scheme signs up with a high reliability and an easy use. The new...
Herbsttagung 2004: Informationstagung Motoren Abschluss- und Zwischenberichte der Forschungsstellen
Germany
Fall meeting 2004: information conference on engines Final and interim reports of the research centres / Herbsttagung 20...
The Proceedings (volume R526, 2004) of the Information Conference on Engines which has been held on the 23rd September 2004 in Pforzheim/Germany, contains ten final and interim reports. The subjects of the contributions presented were as follow: particulate filter with NOx storage coating; cause study on damage-relevant knocking combustion; spray w...
An inverse method for the aerodynamic design of engine nacelles / Ein inverses Verfahren zum aerodynamischen Entwurf von...
The application of an iterative design method allows the aerodynamic design of isolated and installed engine nacelles subjected to complex aircraft configurations. The method couples a flow solver for the solution of the Euler/Navier-Stokes equations on unstructured grids with a design algorithm which solves the transonic potential equation for sma...
