Preliminary design method for 2D digital gas turbine engine structure

The concept of the digital twin is gaining more attention in aeroengine industry. NASA proposed the "digital thread" concept, which is the basis of the digital twin theory. The German Aerospace Center (DLR) proposed the "rubber engine" concept and completed the development of the digital engine based on this concept. Both concepts are focused on achieving digital engine certification and the implementation of the digital twin in the aircraft gas turbine engine development process. Based on these concepts, this paper focuses on the implementation of a digital gas turbine engine, which includes development design techniques and performance evaluation. A preliminary design method for a 2D digital gas turbine engine structure is carried out, which is the basic first step in this approach. The design process starts with thermal cycle parameters evaluation. Then, a one-dimensional mean-line preliminary design of the engine flow-path is carried out and optimized. Based on the obtained flow-path and blade geometries, a 2D gas turbine engine structure is designed, including the following parts: disks, shafts, casings, and drums. The stress analysis is carried out to meet the strength requirements.