Diffuser nozzle for a gas turbine engine
US11840937B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Dec 17, 2021 |
| Grant date | Dec 12, 2023 |
| Priority date | — |
| Expiry date | Jan 28, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/082
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A diffuser nozzle for a gas turbine engine includes a housing disposed about a nozzle axis and extending between a first nozzle end and a second nozzle end. The housing defines a nozzle duct. A plurality of walls is disposed within the nozzle duct. The plurality of walls subdivides the nozzle duct into a plurality of duct sections. The plurality of walls further defines a plurality of axially-extending duct segments of the nozzle duct such that within a first axially-extending duct segment, the duct cross-sectional area of a first duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section and within a second axially-extending duct segment, the duct cross-sectional area of a second duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.