Abstract
Gas turbine blades are subjected to very high levels of stress and temperature during each engine operating cycle. Superimposed upon this quasy-steady state condition, blades also endure vibrational stresses induced by local perturbations. When characterizing advanced manufacturing candidate materials, conventional fatigue tests (low cycle and high cycle fatigue standard tests independently) fail to represent the complex set of stresses generated in gas turbine blades. Combined cycle fatigue (CCF) laboratory tests comprising LCF and HCF at service high temperatures have been completed on a titanium alloy used in intermediate pressure and high pressure compressor rotor and stator components. The aim of the study was to determine the influence of the combined damage mechanisms on the expected fatigue strength of gas turbine components. Standard test rigs have been modified in order to achieve this new and severe testing scenario. The effect CCF stresses was evaluated at a testing temperature of 350°C. Results showed that the effect of superimposing LCF to HCF should be considered in blade design, especially at fillet radius.
| Original language | English |
|---|---|
| Pages (from-to) | 1809-1814 |
| Number of pages | 6 |
| Journal | Procedia Engineering |
| Volume | 10 |
| DOIs | |
| Publication status | Published - 2011 |
Funding
The authors would like to thank the European Commission FPVI for the financial support of the PREMECCY project and the Spanish Ministry of Science and Innovation (MICYNN).
| Funders | Funder number |
|---|---|
| European Commission FPVI | |
| MICYNN | |
| Ministerio de Ciencia e Innovación |
Keywords
- Combined cycle fatigue
- High temperature fatigue
- Ti 6242
- Turbine blades
