The knowledge management flow and technology system for aircraft engine design are presented, with an emphasis on knowledge acquisition and sharing, implementary method and key technology for knowledge management.
Aiming at the problems that BP algorithm has slow convergence rate and is likely to fall into local minimum point,presents two improved BP algorithm methods:LM(Levenberg-Marquardt)optimization algorithm and SCG(scaled conjugate gradient)algorithm,then the two algorithms were applied to fault diagnosis of aircraft engine rotor and compared with each other in research result,simulation and experiment proved that LM optimization algorithm has higher accuracy,faster convergence rate and better feasibility than the SCG algorithm.
By using this method, the 3-D temperature distribution of the flame tube wall of the combustion chamber of an aeroengine has been simulated successfully.
An investigation setup is presented enabling the determination of the substituting drop diameter in fuel aerosol stream created by aeroengine injectors.
Modelling and lifing of structural materials for future aeroengine components
A non-contact inspection system that can automatically assess the quality of complex engineering components such as turbine blades, has been identified by the aeroengine industry as a requirement in automating the process of proof inspection.
The first article inspection of cast turbine blades is on the critical path of a new aeroengine.