Sealed conical-flat dome for flight engine combustors
US10041676B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 8, 2015 |
| Grant date | Aug 7, 2018 |
| Priority date | — |
| Expiry date | Nov 18, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.