Cooling structure for a turbomachinery component
US10808572B2 · kind B2 · utility
0Cited by
41References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 2, 2018 |
| Grant date | Oct 20, 2020 |
| Priority date | — |
| Expiry date | Oct 17, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine that includes a turbomachinery core operable to produce a core gas flow and that includes a combustor. A first duct is positioned downstream of and in flow communication with the combustor. A component is positioned within the first duct and extends between radially outward and radially inward walls of the first duct. The component that includes a first cooling passageway formed therein. The first cooling passageway extends between an inlet communicating with the first duct and positioned facing towards the turbomachinery core, and an outlet communicating with a pressure sink.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.