Methods and apparatus for cooling gas turbine engine rotor assemblies
US7147440B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 20, 2004 |
| Grant date | Dec 12, 2006 |
| Priority date | — |
| Expiry date | Aug 17, 2024 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2214
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade that includes an airfoil having a leading edge and a trailing edge including a plurality of trailing edge openings, a platform, a shank, and a dovetail, wherein the platform extends between the airfoil and the dovetail and includes a radially outer surface, a radially inner surface, and a recessed area extending at least partially between the radially outer and inner surfaces. The method also comprises coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that cooling air is substantially continuously channeled through the platform recessed area during engine operation to facilitate reducing stresses induced to at least a portion of the airfoil trailing edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.