Rotor for a gas turbine
US6416282B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 12, 2000 |
| Grant date | Jul 9, 2002 |
| Priority date | — |
| Expiry date | Oct 12, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/3015
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor for a gas turbine comprises a multiplicity of rotor blades of which each comprises a blade airfoil, a blade root and a platform arranged between blade airfoil and blade root and each of which, together with the blade root, is pushed into an axial location slot, which is arranged on the outer periphery of a rotor disk, and is releasably retained there in such a way that hollow spaces are formed between the platform and the peripheral surface of the rotor disk, and each of which is supplied, for cooling purposes, with cooling air through at least one cooling air supply passage extending in the rotor disk and emerging into the location slot, which cooling air is fed through the blade root to within the blade airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.