Gas turbine engine rotor sections held together by tie shaft, and with blade rim undercut
US8459943B2 · kind B2 · utility
6Cited by
25References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 10, 2010 |
| Grant date | Jun 11, 2013 |
| Priority date | — |
| Expiry date | Nov 6, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/34
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An integrally bladed rotor is utilized in at least a stage of one of a compressor and turbine section. Airfoils extend radially outwardly from a platform, and there is an undercut inward from the platform at a downstream edge of the airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.