The invention relates to an aircraft nacelle in which an inner fixed structure (201) has a heat exchanger (300), the heat exchanger is filled with a bi-phase heat transfer fluid and includes a duct (302) forming a circuit (304) having a front track, a rear track, a lower track and an upper track (304a-d), and a first complementary track (310a) between a central region of the front track (304a) and a central region of the upper track (304d), a second complementary track (310b) between a central region of the front track (304a) and a central region of the lower track (304c), a second complementary track (310b) between the rear track (304b) and the upper track (304d). A third complementary track (310c) between the rear track (304b) and the lower track (304c), and a fourth complementary track (310d) between the rear track (304b) and a central region of the lower track (304c). By this embodiment of the tracks, even if the aircraft experiences a change in position, through at least one of the tracks, a liquid phase of the heat transfer fluid will flow from the front to the rear and then a gas phase of the heat transfer fluid will flow from the rear to the front.
本发明涉及一种飞行器发动机短舱,在其中的内固定结构(201)具有热交换器(300),该热交换器填充有双相传热流体并且包括形成具有前股道、后股道、下股道和上股道(304a-d)的回路(304)的管道(302)、以及在前股道(304a)与上股道(304d)的中心区之间的第一互补股道(310a)、在前股道(304a)与下股道(304c)的中心区之间的第二互补股道(310b)、在后股道(304b)与上股道(304d)之间的第三互补股道(310c)、以及在后股道(304b)与下股道(304c)的中心区之间的第四互补股道(310d)。通过股道的这种实施方式,即使飞行器经历位置的变化,通过股道中的至少一个,传热流体的液相将从前部流到后部,然后传热流体的气相将从后部流到前部。
Nacelle of aircraft engine comprising improved heat exchanger
飞行器发动机的包括改进的热交换器的短舱
2024-03-01
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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