Gas turbine engine airfoil cooling passage configuration
US10641100B2 · kind B2 · utility
1Cited by
11References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 15, 2015 |
| Grant date | May 5, 2020 |
| Priority date | — |
| Expiry date | Sep 3, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.