本发明涉及一种飞行器发动机的两个环形壁(9,10)之间的密封装置,两个环形壁分别是径向内壁(9)和径向外壁(10),所述两个壁围绕共同轴线(X)彼此同轴地接合。该装置的特征在于:外壁(10)包括轴向端部(15),该轴向端部具有平行于轴线X的大致U形横截面,其开口沿一个方向轴向地定向,并且内壁(9)包括轴向端部(11),该轴向端部具有平行于轴线X的大致U形横截面,其开口沿相反的方向轴向地定向,外壁(10)的U形端部(15)包括环形自由边缘(18),该环形自由边缘轴向地接合在内壁(9)的轴向端部(11)的开口中,并且内壁(9)的U形端部(11)包括环形自由边缘(14),该环形自由边缘轴向地接合在外壁(10)的轴向端部(15)的开口中,使得壁在壁之间限定出具有大致S形的轴向横截面的环形气体通道。

    A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.


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    Title :

    飞行器发动机的两个环形壁之间的密封装置


    Publication date :

    2023-05-30


    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 / F16J Kolben , PISTONS