Turbine airfoil with near-wall leading edge multi-holes cooling
US7520725B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 11, 2006 |
| Grant date | Apr 21, 2009 |
| Priority date | — |
| Expiry date | Sep 19, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An air cooled airfoil used in a gas turbine engine includes a showerhead arrangement to cool the leading edge. A cooling supply cavity supplies cooling air to the airfoil, and is metered into an impingement cavity through at least one metering hole from the cooling supply cavity. A plurality of second impingement cavities are located between the first impingement cavity and the leading edge, and each second impingement cavity includes at least one second metering hole to meter cooling air into the second impingement cavity. Each second impingement cavity includes a plurality of film cooling holes to discharge cooling air to the leading edge surface of the airfoil. The second impingement cavities are located adjacent to each other, with one on the leading edge, another on the pressure side, and the third on the suction side.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.