Cooling arrangement for a turbine component
US8647053B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 9, 2010 |
| Grant date | Feb 11, 2014 |
| Priority date | — |
| Expiry date | Sep 24, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03045
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooled component wall (52) with a combustion gas (36) on one side (56) and a coolant gas (48) with higher pressure on the other side (58). The wall includes a cooling chamber (60) with an impingement cooling zone (62), a convective cooling zone (64), and a film cooling zone (66). Impingement holes (70) admit and direct jets (72) of coolant against the wall, then the coolant passes among heat transfer elements such as channels (76) and fins (78) to the film cooling zone (66) where it passes through holes in the wall that direct a film of the coolant along the combustion side of the wall. The chamber may be oriented with the impingement zone (62) downstream and the film cooling zone (66) upstream, relative to the combustion gas flow (36). This provides two passes of the coolant (84, 79) in opposite directions over the respective opposite sides of the wall (56, 58).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.