Rolls Royce, Munich, Germany
Robert Goraj
Biography
Robert Goraj earned MSc degrees in Mechanical Engineering from AGH University of Science and Technology in Poland in 2003, and from Clausthal Technical University in Germany in 2004, with specializations in closed loop-control, electrical engineering, and systems automation. From 2004 to 2007, he worked at Schaeffler KG as a software development engineer. In 2007, he joined Siemens AG and worked until 2015 as an FEM and CFD simulation engineer on various electromagnetic and electromechanical systems. In 2015, he transitioned internally to Siemens Electric Aircraft, where he focused on the development of electric drives. In 2019, following the Rolls-Royce’s acquisition of the Siemens Electric Aircraft division, he began working for Rolls Royce Electrical on multiple R&D tasks. In 2022, he earned a PhD in fluid dynamics from the Polish Academy of Sciences. In 2025, Rolls-Royce closed down its activities in the Advanced Air Mobility, which led to the termination of his contract. Since 2025, he has been working at the German Aerospace Center as a research associate.
Conferences
Room |
Date |
Hour |
Subject |
|---|---|---|---|
| Room 10 |
19-11-2025 |
5:30 pm – 6:00 pm |
1 Fatigue dimensioning of a bearing cap of an electric motor for a commuter aircraft |
Conferences Details
1 Fatigue dimensioning of a bearing cap of an electric motor for a commuter aircraft
An aircraft propeller is directly connected to the rotor shaft of an electric motor. Rotating components are axially supported by a bearing cap. A semi-analytical parametric (second moment of area dependent) mathematical model is built using the Laplace transform. The model is implemented in MATLAB to dimension the bearing cap. Static, modal, frequency response and transient analyses are performed on semi-analytical base. The determined mechanical stresses and deformations are verified in NX NASTRAN by means of the finite element method (FEM). Structural results are used as an input for fatigue calculations performed according to the analytical strength assessment guideline of the Cooperative Research Association for Mechanical Engineering (the FKM guideline). Based on optimal material utilization, a geometry of the bearing cap is developed. Using the fatigue software RIFEST, it is demonstrated that the analyzed geometry can withstand 1E7 load cycles due to propeller excitation