Gas turbine engine rotor assembly and method of assembling the same
US9896946B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Oct 31, 2013 |
| Grant date | Feb 20, 2018 |
| Priority date | — |
| Expiry date | Jul 23, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49321
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor assembly includes a rotor disc including a plurality of circumferentially-spaced diskposts and a plurality of dovetail slots. Each dovetail slot is defined between a pair of circumferentially-adjacent diskposts. A plurality of rotor blades are coupled to the rotor disc. Each rotor blade includes a dovetail portion that is configured to slidably engage a respective dovetail slot. A plurality of platform sections are coupled to the rotor disc such that each platform section is adjacent a respective rotor blade. Each platform section includes a diskpost slot that is configured to receive one of the plurality of diskposts such that each dovetail slot receives a respective dovetail portion and at least a portion of at least one of the platform sections adjacent the rotor blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.