在例如为飞行器发动机的机舱罩的壁(1)下方延伸的热交换回路的出口(2)被分成呈平行狭槽形式的开口(7),这些开口沿纵向方向(X)是细长的并且沿横向方向(T)相继布置,以将热气分成多股流(9),同时促进源自外部流(10)的新鲜气流(11)在中间层压板(8)上的流通。热气不会轻易地落回到壁(1)的外部面上,并且不会有损坏所述壁的风险,并且所述气体与新鲜的室外空气更有效地混合。开口设置有沿横向方向(T)和下游纵向方向(X)扩口的喷嘴(15),以促进热气流和冷气流的混合。

    The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.


    Access

    Download


    Export, share and cite



    Title :

    飞行器发动机的热气管的、穿过发动机壁的出口


    Publication date :

    2023-03-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke