Turbine endwall with grooved recess cavity
US8376705B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 9, 2011 |
| Grant date | Feb 19, 2013 |
| Priority date | — |
| Expiry date | Sep 9, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2214
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A vane assembly for a gas turbine engine including an endwall and an airfoil extending from the endwall. An inner rail extends radially inwardly of the endwall, and an overhang portion extends axially from a location of the inner rail to a downstream edge. A recess cavity is defined in the overhang portion between the inner rail and the downstream edge. The recess cavity extends radially into the overhang portion and defines a cavity surface. A plurality of grooves extend radially into the cavity surface and have an elongated dimension extending in a direction from the inner rail toward the downstream edge. A plurality of cooling passages extend axially through the overhang portion, and are located between the grooves.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.