Interlaminar stress reducing configuration for composite turbine components
US9004874B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Feb 22, 2012 |
| Grant date | Apr 14, 2015 |
| Priority date | — |
| Expiry date | Aug 30, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/6033
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbomachinery blade includes: an airfoil; and a shank extending from a root of the airfoil, the shank being constructed from a composite material including reinforcing fibers embedded in a matrix The shank includes a pair of spaced-apart side faces that cooperatively define: a dovetail disposed at a radially inboard end of the shank, comprising spaced-apart, diverging faces; a first neck portion having a concave curvature disposed radially outboard of the dovetail, and defining a primary minimum neck at which a thickness of the shank is at a local minimum; and a second neck portion disposed radially outboard of the first minimum neck, the second neck portion having a concave curvature and defining a secondary minimum neck at which the thickness of the shank is at a local minimum.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.