Thermal shielding in a gas turbine
US10443402B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 7, 2016 |
| Grant date | Oct 15, 2019 |
| Priority date | — |
| Expiry date | Nov 16, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade includes a labyrinth of internal channels for the circulation of coolant received through an inlet formed in a terminal portion of the blade root and leading to a duct-defined wall. A first passage intersects the duct and extends through the blade towards a tip. An end of the first passage is arranged to capture incoming coolant flow. A second passage intersects the duct at a position downstream of the first passage intersection. The duct and/or the passage intersections are configured to create a pressure drop in the duct in the direction from the inlet to the second passage intersection. In an axial direction, a duct wall terminates at a position between the inlet and the second passage intersection.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.