Cooled airfoils for a gas turbine engine
US5702232A · kind A · utility
151Cited by
10References
4Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 13, 1994 |
| Grant date | Dec 30, 1997 |
| Priority date | — |
| Expiry date | Dec 13, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An internally cooled airfoil for a gas turbine engine includes a leading edge region, a mid-chord region, a transition region, and a trailing edge region. The mid-chord region has a double wall configuration with the two outer walls and two inner walls. The trailing edge region has a conventional single wall configuration. The transition region has a three wall configuration designed to provide a gradual transition from the four wall configuration to the two wall configuration and to minimize high stresses therein.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.