The invention relates to a propulsion unit for an aircraft and to an aircraft comprising at least one such propulsion unit. The propulsion unit comprises a motor (32), a system (40) for supplying fuel to the motor, a cowl (46) inside which at least a portion of the motor (32) and the fuel supply system (40) are positioned, and a structure configured at the cowl (46) when the pressure in the internal region is greater than or equal to a given threshold value or when a leak is detected and at least one pressure relief device (54) establishing communication between the inner region and the outer region. Activation of the pressure relief device makes it possible to limit the risk of damage to the cowl (46) due to possible overpressure phenomena inside the cowl.
本发明涉及飞行器的推进单元和包括至少一个这种推进单元的飞行器。该推进单元包括马达(32)、用于向马达供应燃料的系统(40)、马达(32)和燃料供应系统(40)的至少一部分定位在其内部的整流罩(46)以及构造成在内部区域中的压力大于或等于给定阈值时或者在检测到泄漏时在整流罩(46)的内部区域与外部区域之间建立连通的至少一个压力释放装置(54)。压力释放装置的启用使得可以限制由于整流罩内部可能的过压现象而损坏整流罩(46)的风险。
Propulsion unit for aircraft and aircraft comprising at least one such propulsion unit
飞行器的推进单元和包括至少一个这种推进单元的飞行器
2024-08-23
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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