Aerial turbofan engine flight envelope right boundary force application oil supply method and device
By adjusting the nozzle throat area and calculating the flow rate at each working point on the right boundary of the flight envelope of the aeronautical turbofan engine, the control rules for the afterburner oil supply were determined, the problem of failure to achieve optimal design of the thrust was solved, and the thrust of the entire aircraft and the maneuverability of the aircraft were improved.
Patent Information
- Application Number
- CN202411832041.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-12
- Publication Date
- 2025-03-18
- Estimated Expiration
- 2044-12-12
AI Technical Summary
When the existing aerospace turbofan engine is on the right boundary of the flight envelope, the thrust fails to achieve the optimal design, resulting in low thrust and long horizontal acceleration time, which in turn reduces the maneuverability of the aircraft.
By determining the nozzle throat area adjustment range for each working point on the right boundary of the flight envelope, multiple nozzle throat area points are discrete within this range, the engine inlet air flow and external culvert air flow at each point are calculated, the air flow involved in combustion and the total fuel flow are determined, and the full force thrust is finally calculated, and the nozzle throat area point corresponding to the maximum value is selected as the force oil supply control rule.
The optimal thrust design of the entire aircraft is achieved on the right boundary of the flight envelope, which improves the thrust of the entire aircraft, reduces the aircraft's horizontal acceleration time, and improves the aircraft's maneuverability.