Nozzle arrangement for a gas turbine engine
US10371094B2 · kind B2 · utility
2Cited by
38References
18Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jul 1, 2015 |
| Grant date | Aug 6, 2019 |
| Priority date | — |
| Expiry date | Nov 29, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; and, a mixer duct defined by a mixer fairing and having a mixer nozzle, wherein the mixer duct is arranged to receive an airflow from the bypass duct through a mixer duct inlet and an airflow from the engine core, when in use, and the geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.