Passage geometry for gas turbine engine combustor
US10684017B2 · kind B2 · utility
16Cited by
18References
7Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 21, 2014 |
| Grant date | Jun 16, 2020 |
| Priority date | — |
| Expiry date | Jul 31, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.