Trailing edge cooling system in a turbine airfoil assembly
US8840363B2 · kind B2 · utility
Assignees
Inventor
Key dates
| Filing date | Sep 9, 2011 |
| Grant date | Sep 23, 2014 |
| Priority date | — |
| Expiry date | Oct 9, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a plurality of cooling fluid passages. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include zigzagged passages that include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.