The invention relates to a shunting ring anti-icing device for an aero-engine, comprising: a shunting ring body, the shunting ring body comprising a shunting ring front portion, a shunting ring rear portion and a first matching portion, the shunting ring rear portion comprising a first flange portion; the stator casing is positioned in the radial inner part of the shunt ring body and comprises a second flange part and a third flange part, and a second matching part is formed at the radial outer end of the second flange part; the oil collecting cavity is defined by the flow dividing ring body and the stator casing in a sealed mode, the first matching part is matched with the second matching part in a sealed mode, and the first flange part is matched with the third flange part in a sealed mode; and the oil guide pipe allows the lubricating oil to enter the oil collecting cavity and allows the lubricating oil circularly passing through the oil collecting cavity to leave the oil collecting cavity. The anti-icing structure of the engine is optimized, the reliability of the anti-icing device is improved, and the performance and the heat efficiency of the engine are improved. The invention further relates to an aero-engine comprising the shunt ring anti-icing device.
本发明涉及一种用于航空发动机的分流环防冰装置,包括:分流环本体,分流环本体包括分流环前部、分流环后部以及第一配合部,其中,分流环后部包括第一法兰部;静子机匣,静子机匣定位在分流环本体的径向内部,并且包括第二法兰部和第三法兰部,第二法兰部的径向外端形成第二配合部;集油腔,集油腔由分流环本体和静子机匣封围形成,其中,第一配合部与第二配合部密封配合并且第一法兰部与第三法兰部密封配合;以及导油管,导油管允许润滑油进入集油腔,并且允许循环通过集油腔的润滑油离开集油腔。本发明优化了发动机防冰结构,提高了防冰装置的可靠性,提高发动机性能和热效率。本发明还涉及包括这种分流环防冰装置的航空发动机。
Shunting ring anti-icing device for aero-engine and aero-engine
用于航空发动机的分流环防冰装置和航空发动机
2025-05-30
Patent
Electronic Resource
Chinese
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