Gas turbine engine component suction side trailing edge cooling scheme
US7465154B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 18, 2006 |
| Grant date | Dec 16, 2008 |
| Priority date | — |
| Expiry date | Apr 6, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/22141
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component has a cooling scheme that utilizes an impingement tube to cool the suction wall and the pressure wall of a mid portion of an airfoil. The impingement tube is formed to not have impingement holes on an end of the impingement tube spaced toward the trailing edge along the suction wall. Impingement holes are formed in the same portion on a side of the impingement tube facing the pressure wall. Pedestals extend from an inner face of the suction wall toward the impingement tube in this area. The use of the pedestals over this area provides greater cooling to a focused area on the suction wall of the airfoil that might otherwise receive inadequate film cooling.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.