Integral nozzle and shroud
US6530744B2 · kind B2 · utility
47Cited by
14References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 29, 2001 |
| Grant date | Mar 11, 2003 |
| Priority date | — |
| Expiry date | May 29, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component including a nozzle outer band, a plurality of nozzle vanes extending inward from the outer band, and an inner band extending circumferentially around inner ends of the vanes. Further, the component has a shroud integral with the outer band adapted for surrounding a plurality of blades mounted in the engine for rotation about a centerline thereof.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.