Injector nose for turbomachine including a secondary fuel swirler with changing section
US11168886B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 27, 2019 |
| Grant date | Nov 9, 2021 |
| Priority date | — |
| Expiry date | Dec 27, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/11101
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An injector nose for a turbomachine includes a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis (44), and a secondary fuel circuit (64) comprising a secondary fuel swirler (114) formed of swirler channels (112) opening into a terminal fuel ejection portion (68) of annular shape arranged around the fuel ejection nozzle. Each swirler channel (112) has a passage section which decreases in a direction going from an upstream end (111) to a downstream end (115) of the swirler channel (112). The reduction of the passage section of the swirler channels (112) makes it possible to increase the head loss between the inlet and the outlet of the secondary fuel swirler (114) and thus notably to accelerate the fuel within the secondary fuel swirler, while allowing lower fuel flow rates.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.