Cooling layout for a turbine blade, turbine blade included therein, turbine and aircraft engine equipped therewith
US7658591B2 · kind B2 · utility
8Cited by
6References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 6, 2006 |
| Grant date | Feb 9, 2010 |
| Priority date | — |
| Expiry date | Mar 4, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A layout for cooling a blade having a cavity surrounded by an internal wall including cooling fins which are spaced apart from each other by a pitch (p) and each have a thickness (e). The blade has, inside the cavity, a jacket passed through by emission holes each having a diameter (d). When the jacket is in place in the cavity of the blade, and in respect of the critical operating point of the turbine engine, each emission hole of the jacket is opposite a place on the internal wall of the blade which is located between cooling fins.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.