Accelerator insert for a gas turbine engine airfoil
US10443407B2 · kind B2 · utility
1Cited by
23References
29Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 15, 2016 |
| Grant date | Oct 15, 2019 |
| Priority date | — |
| Expiry date | Jun 15, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.