Turbine vane for a gas turbine engine having serpentine cooling channels
US8328518B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 13, 2009 |
| Grant date | Dec 11, 2012 |
| Priority date | — |
| Expiry date | Apr 14, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/22141
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine vane for a gas turbine engine having an internal cooling system formed from at least one serpentine cooling channel with enhanced cooling elements. The serpentine cooling channel may include a first turn manifold with purge air discharge orifices inline with a first pass of the serpentine cooling channel. Cooling fluids may be used to cooling the leading edge of the vane and passed through the purge air discharge orifices to purge the rim cavity proximate to the endwall. The first turn manifold may also include a plurality of trip strips. The trips strips may be positioned on the suction and pressure sidewalls and may be offset from trip strips on the opposing sidewall. The cooling system may also include an aft purge rim orifice.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.