Rotor of a turbine of a gas turbine with improved cooling air routing
US10082031B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 3, 2016 |
| Grant date | Sep 25, 2018 |
| Priority date | — |
| Expiry date | Oct 12, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor of a turbine of a gas turbine, having a rotor hub and a plurality of blade platforms, each carrying at least one turbine blade, and having one each cooling air chamber for passing cooling air formed by adjacent blade platforms. At least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms. The cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.