Gas turbine vane with cooling channel end turn structure
US8821111B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 14, 2010 |
| Grant date | Sep 2, 2014 |
| Priority date | — |
| Expiry date | Jun 1, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/185
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A vane structure for a gas turbine engine. The vane structure includes a radially outer platform and a radially inner platform, and an airfoil having an outer wall extending radially between the outer platform and the inner platform. A cooling passage is defined within the outer wall and has a plurality of radially extending channels. An outer end turn structure is located at the outer platform to conduct cooling fluid in a chordal direction between at least two of the channels. The outer end turn structure includes an enlarged portion wherein the enlarged portion is defined by an enlarged dimension, in a direction transverse to the chordal direction, between the at least two channels.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.