Composite integrally bladed rotor
US6881036B2 · kind B2 · utility
7Cited by
5References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 3, 2002 |
| Grant date | Apr 19, 2005 |
| Priority date | — |
| Expiry date | Dec 12, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/603
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present invention relates to an integrally bladed rotor for use in a gas turbine engine. The integrally bladed rotor comprises a plurality of pairs of airfoil blades. Each pair of blades has a spar which extends from a first tip of a first one of the airfoil blades in the pair to a second tip of a second one of the airfoil blades in the pair. The rotor further comprises an outer shroud integrally joined to the first and second tips in each pair of airfoil blades and an inner diameter hub.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.