Rotor assembly disk spacer for a gas turbine engine
US9145771B2 · kind B2 · utility
4Cited by
52References
6Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jul 28, 2010 |
| Grant date | Sep 29, 2015 |
| Priority date | — |
| Expiry date | Jun 12, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A disk spacer for a gas turbine engine includes a rim, a bore, a web and a load path spacer. The web extends between the rim and the bore. The load path spacer is positioned between the rim and the bore.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.