一种微型涡喷发动机快速起动独立供油点火系统
By designing independent fuel supply and oxygen replenishment units, the problem of unstable ignition during the start-up of micro turbojet engines has been solved, achieving rapid start-up and high-altitude stability, expanding application scenarios, and meeting the needs of in-flight start-up and multiple start-stop operations.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- 西安觉天动力科技有限责任公司
- Filing Date
- 2025-07-31
- Publication Date
- 2026-07-17
AI Technical Summary
Existing micro turbojet engines have strict requirements for air temperature and speed during the starting process, which results in low ignition head temperature and inability to ignite, unstable starting process, and inability to quickly restart at high altitudes or in the air, thus limiting their application scenarios.
It adopts an independent fuel supply unit and oxygen supply unit, including an independent fuel pump, an independent solenoid valve, an ignition atomizing nozzle, an oxygen supply tank and a jet ring. Through fuel mist injection and high-pressure oxygen supply, it ensures sufficient oxygen in the combustion chamber, achieving rapid ignition and stable combustion.
It has achieved rapid start-up and high-altitude stability of micro turbojet engines, expanded application scenarios, met the requirements of in-flight start-up and multiple start-stop operations, and improved the engine's compatibility and versatility.
Smart Images
Figure CN120667259B_ABST