Gas turbine engine combustor comprising air inlet tubes arranged around the combustor
US10823418B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 2, 2017 |
| Grant date | Nov 3, 2020 |
| Priority date | — |
| Expiry date | Apr 5, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a turbine engine includes an inner combustion liner and an outer combustion liner together defining at least in part an interior. The interior includes a combustion chamber and a main portion. The combustor also includes an inlet combustion liner at least partially defining the combustion chamber of the interior and including an inlet assembly. The inlet assembly includes at least two cavity air tubes arranged along the axial direction, each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.