Methods and apparatus for cooling gas turbine engine rotor assemblies
US7189063B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Sep 2, 2004 |
| Grant date | Mar 13, 2007 |
| Priority date | — |
| Expiry date | Dec 4, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for assembling a rotor assembly for gas turbine engine is provided. The method includes providing a first rotor blade that includes an airfoil, a platform, a shank, and a dovetail. The airfoil extends radially outward from the platform, the shank extends radially inward from the platform, and the dovetail extends from the shank, forming a recess within a portion of the shank. The method also includes coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that a shank cavity is defined between the first and second rotor blade shanks. During operation, cooling air may enter and pressurize the shank cavity through the recessed portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.