Gas turbine engine fan blade retention
US5913660A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jul 1, 1997 |
| Grant date | Jun 22, 1999 |
| Priority date | — |
| Expiry date | Jul 1, 2017 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fan for a gas turbine engine comprises a rotary disc carrying an annular array of radially extending fan blades. Each fan blade has a root portion which is radially constrained within a generally axially extending groove formed within a disc rim. The blade root comprises two portions each radially convergent toward one another with respect to the axis of rotation of the disc. The groove within the disc also comprises two base portions each being correspondingly radially convergent toward one another. Axial retention of the blade root within the groove is achieved by the centrifugal component of the blade load acting in an opposite direction to any applied axial load in the forward or rearward direction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.