Apparatus for cooling rotating blades in a gas turbine
US5117626A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 4, 1990 |
| Grant date | Jun 2, 1992 |
| Priority date | — |
| Expiry date | Sep 4, 2010 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2212
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus and method are provided for cooling the rotating blades in the turbine section of a gas turbine. Cooling of the leading edge is accomplished by forming a radial passageway in the leading edge portion of the blade airfoil. Rows of holes along the leading edge of the blade airfoil allow cooling air to flow from the radial passageway to the surface of the leading edge, thereby cooling the leading edge portion of the airfoil. The flow area of the radial passageway reduces as it extends radially outward so that the velocity of the cooling air flowing through the passageway is maintained. A plenum formed in the root portion of the blade distributes cooling air to small diameter holes in the center and trailing edge portion of the airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.