visualized and expanded in Microsoft Windows environment
was introduced in this paper.In this framework program
the user could click engine components graphically shown in the component library
and drag them to the working space to form any kind of aircraft engine intended for simulation.The present framework covers steady and transient state performance calculation functions.The performance calculation of some sample aircraft engines confirms the correctness of the logic in this program and the practicability of the graphical user interface.
Development path and future trend of carrier-based advanced trainer engine
Thermal protection effectiveness of thermal barrier coatings in turbine blade applications
Aero-engine cycle design approach for multiple operating conditions performance reliability
Relationship between rotor/vanes blade number andnodal diameter number of bladed-disk coupling vibration
ptimum design of rotor structure layout and its mechanical properties
Related Author
PENG Yunlong
WU Xiong
DING Ting
ZHU Jianqin
ZHAO Chaofan
QIU Lu
曹大录
白广忱
Related Institution
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics