Liner of a gas turbine engine combustor including dilution holes with airflow features
US10890327B2 · kind B2 · utility
2Cited by
27References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 14, 2018 |
| Grant date | Jan 12, 2021 |
| Priority date | — |
| Expiry date | Oct 14, 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 combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.