Serpentine cored airfoil with body microcircuits
US8511994B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 23, 2009 |
| Grant date | Aug 20, 2013 |
| Priority date | — |
| Expiry date | Oct 1, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/204
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component has an airfoil that extends from a leading edge to a trailing edge, and a suction side and has a pressure side. There are cooling passages extending from a root of the airfoil toward a tip of the airfoil. The cooling passages include a straight passage extending from the root toward the tip and adjacent the leading edge. A serpentine passage has at least three connected paths and is spaced from the straight passage toward the trailing edge. A cooling circuit is provided between the pressure wall and each of the three serpentine paths, and the straight path. A cooling circuit is provided between the suction wall and the straight passage. There is no cooling between at least a downstream one of the at least three paths of the serpentine passage and the suction wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.