Turbomachine blade with fluidically cooled shroud
US7427188B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 14, 2007 |
| Grant date | Sep 23, 2008 |
| Priority date | — |
| Expiry date | Mar 14, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbomachine blade, in particular a turbine blade of a gas turbine includes a blade root with a cooling-fluid feed, a blade tip formed with a shroud element. At least one throughflow passage which extends in the blade longitudinal direction is arranged inside the airfoil. A shroud cooling passage is formed in the shroud element at least along a section of the latter, the shroud cooling passage being connected via an opening to the throughflow passage, and a cooling fluid flowing through this shroud cooling passage during operation of the turbomachine blade. At least one flow-guiding element for guiding at least some of the cooling-fluid flow flowing through the shroud cooling passage is arranged in the shroud cooling passage and/or in an inflow or outflow to or from the shroud cooling passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.