Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor
US10648666B2 · kind B2 · utility
8Cited by
15References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 16, 2014 |
| Grant date | May 12, 2020 |
| Priority date | — |
| Expiry date | May 6, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.