Turbine component with axially spaced radially flowing microcircuit cooling channels
US7775768B2 · kind B2 · utility
36Cited by
10References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 6, 2007 |
| Grant date | Aug 17, 2010 |
| Priority date | — |
| Expiry date | Nov 10, 2028 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/21
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine component such as a turbine blade or a vane includes at least one microcircuit cooling channel having a plurality of sub-channels extending along a radial direction of the airfoil. The plurality of channels are axially spaced, and are fed by radially spaced inlets.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.