Turbine vane for a gas turbine engine having serpentine cooling channels with internal flow blockers
US8511968B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 13, 2009 |
| Grant date | Aug 20, 2013 |
| Priority date | — |
| Expiry date | Oct 1, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/221
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine vane for a gas turbine engine with an internal cooling system formed from a serpentine cooling channel with one or more flow blocking ribs is disclosed. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling channels may include flow blocking ribs to form concurrent flow channels to reduce the cross-sectional area within the midchord region of the airfoil to maintain the internal through flow channel Mach number. The flow blocking ribs may include slots therein and may have any appropriate configuration. In at least one embodiment, the flow blocking ribs may be have a nonuniform taper or a uniformed taper.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.