Turbine blade platform trailing edge undercut
US8287241B2 · kind B2 · utility
9Cited by
4References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 21, 2008 |
| Grant date | Oct 16, 2012 |
| Priority date | — |
| Expiry date | Mar 18, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/304
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine blade having reduced stresses around a regions where the airfoil training edge joins the platform is disclosed. The lower stresses are achieved due to an undercut region proximate the blade trailing edge being placed in the platform. The undercut region has a compound fillet radius formed from two single and tangent radii where the first radius closer to the airfoil is larger than the second radius such that a ratio of R1/R2 is approximately 2.0 to 2.5.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.