Blade for a turbo machine having labyrinth seal cooling passage
US9341078B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 8, 2011 |
| Grant date | May 17, 2016 |
| Priority date | — |
| Expiry date | Nov 18, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade for a turbomachine, for example a gas turbine, is provided. The blade is arranged on a turbine rotor of the gas turbine. The blade includes a root portion having two narrow sides and two broad sides, a cooling air supply passage in the root portion, and a cooling air bleed which is arranged in the root portion and is in fluid connection with the cooling air supply passage. The cooling air bleed includes a nozzle on one of the narrow sides of the root portion, wherein the nozzle is formed by a hole and wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.