Abstract
A predictive procedure capable of calculating dovetail surface contact loads in gas turbine engines is developed. The procedure determines contact normal and tangential loads, for a complete mission involving radial blade and blade/disk thermal loads. Once Finite Element calculations to determine empirical constants for a specific blade/disk geometry are completed, the predictive procedure handles complicated load histories in near real-time for both single and double tang dovetails. The predictive model determines the load split between the top and bottom tang from the empirical constants, with the predicted load split the contact loads on individual tangs can be determined. Results are within 5-10% for missions that include speed and thermal variation.
| Original language | American English |
|---|---|
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| State | Published - Jul 4 2008 |
| Externally published | Yes |
| Event | 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference - Schaumburg, IL, United States Duration: Apr 7 2008 → Apr 10 2008 |
ASJC Scopus subject areas
- Architecture