Hybrid-composite gas turbine exhaust nozzle compression link
US6240720A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 9, 1999 |
| Grant date | Jun 5, 2001 |
| Priority date | — |
| Expiry date | Sep 9, 2019 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A hybrid-composite gas turbine exhaust nozzle compression link is formed as an elongated hollow tubular cylindrical shell having an axis of elongation. In cross section taken perpendicular to the axis of elongation, the shell has a structure of an inner rim of an inner-rim titanium-base alloy, a reinforcing layer having reinforcing fibers such as silicon carbide fibers extending parallel to the axis of elongation and embedded in a matrix titanium-base alloy, and an outer rim of an outer-rim titanium-base alloy. The titanium-base alloys are typically of the same nominal composition. Attachment fittings are present at each end of the shell.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.