Turbine airfoil with outer wall cooling system and inner mid-chord hot gas receiving cavity
US7303376B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Dec 2, 2005 |
| Grant date | Dec 4, 2007 |
| Priority date | — |
| Expiry date | Feb 25, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/187
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine airfoil usable in a turbine engine and having at least one cooling system. The cooling system may be positioned in an outer wall of the turbine airfoil, and the airfoil may include a hot gas receiving cavity positioned in a mid-chord region of the airfoil. The hot gas receiving cavity may have an opening in a tip of the airfoil to enable hot gases to circulate into the hot gas receiving cavity. In at least one embodiment, the cooling system in the outer wall and the hot gas receiving cavity may include a plurality of ribs. Cooling fluids may be passed through the cooling system in the outer wall, and hot combustion gases may be passed into the hot gas receiving cavity to moderate the temperature of the inner portions of the outer wall to reduce the temperature gradient in the outer wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.