Resupply hole of cooling air into gas turbine blade serpentine passage
US10378363B2 · kind B2 · utility
0Cited by
6References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 10, 2017 |
| Grant date | Aug 13, 2019 |
| Priority date | — |
| Expiry date | Dec 9, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.