Abstract
This paper examines the incorporation of a damage prediction model into the control systems synthesis of an aircraft gas turbine engine, with the objective of extending the life of critical engine components while maintaining the required level of system performance. Turbine blades are used as an example, with the primary modes of damage being high-cycle fatigue and low-cycle thermomechanical fatigue.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 4700-4701 |
| Number of pages | 2 |
| Journal | Proceedings of the IEEE Conference on Decision and Control |
| Volume | 5 |
| State | Published - 1997 |
| Event | Proceedings of the 1997 36th IEEE Conference on Decision and Control. Part 1 (of 5) - San Diego, CA, USA Duration: Dec 10 1997 → Dec 12 1997 |
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering
- Modeling and Simulation
- Control and Optimization