Method and apparatus for cooling gas turbine rotor blades
US7165940B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 10, 2004 |
| Grant date | Jan 23, 2007 |
| Priority date | — |
| Expiry date | Jun 10, 2024 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/187
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine includes a leading edge, a trailing edge a tip plate, a first sidewall extending in radial span between an airfoil root and the tip plate, and a second sidewall connected to the first sidewall at the leading edge and the trailing edges, to define a cooling cavity therein. The sidewall extends in radial span between the airfoil root and the tip plate. The airfoil also includes a plurality of longitudinally spaced apart trailing edge cooling slots arranged in a column extending through the first sidewall. The slots are in flow communication with the cooling cavity and arranged in a non-uniform distribution along the trailing edge so that the number of slots in at least one portion of the trailing edge is greater than a different portion of the trailing edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.