초록 ▼

Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct

Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.

대표청구항 ▼

We claim: 1. A cooling system for an aircraft comprising: an engine nacelle including an airflow inlet; an engine housed in the engine nacelle in flow communication with the airflow inlet; a bypass duct extending between the engine nacelle and the engine in flow communication with the airflow inlet

We claim: 1. A cooling system for an aircraft comprising: an engine nacelle including an airflow inlet; an engine housed in the engine nacelle in flow communication with the airflow inlet; a bypass duct extending between the engine nacelle and the engine in flow communication with the airflow inlet, the bypass duct including an outer wall having an opening formed therein; and a heat exchanger integrated with the engine and disposed outside of the bypass duct over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle and having a wall that is integrally formed with the bypass duct outer wall, the heat exchanger includes a bypass flow path air inlet, an engine air inlet, a first outlet, and a second outlet, the bypass flow path air inlet providing flow communication between the bypass flow path and the first outlet, the engine air inlet providing flow communication between the engine and the second outlet. 2. The cooling system of claim 1, wherein: the engine air inlet is configured to receive air and the bypass flow path air inlet is configured to receive air that has a temperature cooler than the air received by the engine air inlet; and the heat exchanger is configured to allow energy exchange between the air received by the engine air inlet and the air received by the bypass flow path air inlet. 3. The cooling system of claim 2, further comprising a plurality of fins disposed in the bypass flow path air inlet. 4. The cooling system of claim 3, wherein one fin of the plurality of fins includes an angled flange configured to direct air toward the heat exchanger. 5. The cooling system of claim 3, wherein the plurality of fins is configured to selectively open and close to regulate airflow through the bypass flow path air inlet. 6. The cooling system of claim 1, further comprising a bypass flow path valve disposed downstream of the bypass flow path and configured to selectively open and close to regulate airflow through the heat exchanger. 7. The cooling system of claim 6, wherein the bypass flow path valve is disposed in the opening of the bypass duct outer wall. 8. The cooling system of claim 1, further comprising an engine flow path valve disposed downstream of the engine and configured to selectively open and close to regulate airflow through the heat exchanger. 9. The cooling system of claim 1, wherein at least a portion of the heat exchanger is integrally formed with the bypass duct outer wall. 10. A cooling system for an aircraft comprising: an engine nacelle including an airflow inlet; an engine housed in the engine nacelle in flow communication with the airflow inlet; a bypass duct extending between the engine nacelle and the engine in flow communication with the airflow inlet, the bypass duct including an outer wall having an opening formed therein; a heat exchanger disposed outside of the bypass duct between the bypass duct outer wall and the engine nacelle, the heat exchanger disposed on the bypass duct outer wall in communication with the opening thereof and including a bypass flow path air inlet, an engine air inlet, a first outlet, and a second outlet, the bypass flow path air inlet in flow communication with the bypass flow path and the first outlet, the engine air inlet in flow communication with the engine and the second outlet; and a bypass flow path valve disposed downstream of the bypass flow path air inlet and configured to selectively open and close to at least partially regulate airflow through the heat exchanger. 11. The cooling system of claim 10, wherein the bypass flow path valve is disposed in the opening of the bypass duct outer wall. 12. The cooling system of claim 10, wherein a bypass flow path valve is disposed downstream of the heat exchanger first outlet. 13. The cooling system of claim 10, further comprising an engine flow path valve disposed downstream of the engine and configured to selectively open and close to regulate airflow through the heat exchanger. 14. A cooling system for an aircraft comprising: an engine nacelle including an airflow inlet; an engine housed in the engine nacelle in flow communication with the airflow inlet; a bypass duct extending between the engine nacelle and the engine in flow communication with the airflow inlet, the bypass duct including an outer wall having an opening formed therein; and a heat exchanger disposed outside of the bypass duct between the bypass duct outer wall and the engine nacelle and having a wall that is integrally formed with the bypass duct outer wall, the heat exchanger in flow communication with the bypass duct outer wall opening and including a bypass flow path air inlet, an engine air inlet, a first outlet, and a second outlet, the bypass flow path air inlet providing flow communication between the bypass flow path and the first outlet, and the engine air inlet providing flow communication between the engine and the second outlet. 15. The cooling system of claim 14, further comprising an engine flow path valve disposed downstream of the engine and configured to selectively open and close to regulate airflow through the heat exchanger. 16. The cooling system of claim 15, wherein the engine flow path valve is disposed between the engine and the heat exchanger engine air inlet. 17. The cooling system of claim 15, wherein an engine flow path valve is disposed downstream of the heat exchanger second outlet. 18. The cooling system of claim 14, further comprising a bypass flow path valve disposed downstream of the bypass flow path air inlet and configured to selectively open and close to regulate airflow through the heat exchanger. 19. The cooling system of claim 18, wherein the bypass flow path valve is disposed in the opening of the bypass duct outer wall. 20. The cooling system of claim 14, wherein a bypass flow path valve is disposed downstream of the heat exchanger first outlet.