Gas turbine and rotor blade for a turbomachine
US7416394B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 4, 2004 |
| Grant date | Aug 26, 2008 |
| Priority date | — |
| Expiry date | Aug 2, 2025 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/147
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
The invention relates to a rotating blade for a turbomachine which can be cross flown by a flow medium, especially for a gas turbine which can be cross flown by a working fluid. The gas turbine comprises a rotating blade base, a platform region which extends in a perpendicular manner thereto and a curved blade profile all of which are arranged in a successive manner. The blade profile extends from a front edge, against which a liquid can flow, to a rear edge between which a suction side and a pressure side of the blade profile are formed by means of a relief slot comprising a longitudinal extension in the blade profile. In order to produce a rotating blade which has increased durability, the relief slot on the end of the blade profile oriented towards the platform region is arranged in the region of the rear edge, extending through the blade profile from the suction side to the pressure side and the longitudinal extension thereof is oriented in an essentially transversal manner in relation to the direction of flow of the working fluid.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.