LUBRICATION OR COOLING CIRCUIT OF AN AIRCRAFT ENGINE AND AIRCRAFT ENGINE WITH SUCH A COOLING CIRCUIT
Patent Information
- Application Number
- DE602019064276
- Authority / Receiving Office
- DE · DE
- Patent Type
- Patents
- Current Assignee / Owner
- Priority Date
- 2018-08-10
- Filing Date
- 2019-08-06
- Publication Date
- 2025-01-01
- Estimated Expiration
- 2039-08-06
AI Technical Summary
Existing aircraft propulsion engine cooling systems, particularly those with high dilution ratios and reduction gearboxes, face challenges in reducing fuel consumption and engine thrust while maintaining effective cooling, as they often cause pressure losses and airflow disturbances when using finned heat exchangers or bleeding air from the secondary flow.
A smooth skin exchanger is housed between the fan and rectifier arms, utilizing the strong turbulence in this area for thermal exchanges between the fluid circuit and secondary air flow, without disturbing the airflow or increasing fuel consumption, and is designed to be curved to match the engine's exterior casing, maximizing heat transfer.
This solution enhances cooling capacity, reduces the impact on engine performance and fuel consumption, and increases engine thrust by leveraging the turbulent air flow for efficient heat exchange, making it suitable for high-dilution ratio engines and reduction gearboxes.