The invention relates to an air intake (1) of a turbojet engine nacelle comprising an annular structure (110) including an outer fairing (100) defining an aerodynamic outer surface and an inner fairing (102) defining an aerodynamic inner surface, the outer (100) and inner (102) fairings being connected upstream by an air intake lip (108) forming a leading edge, the inner fairing (102) comprising an outer skin (114) fixed to the air intake lip (108) by means of an upstream fixation flange (118), the outer skin (114) being intended to be fixed to an outer fan casing (116) by means of a downstream fixation flange (122), the air intake (1) comprising at least one independent acoustic panel (2) attached to the outer skin (114) and comprising a perforated acoustic skin (200) and a cellular core (202).

    本发明涉及一种涡轮喷气发动机机舱的进气道(1),所述进气道包括环形结构(110),所述环形结构包括限定外部空气动力学表面的外部整流罩(100)和限定内部空气动力学表面的内部整流罩(102),所述外部整流罩(100)和所述内部整流罩(102)通过形成前缘的进气道唇缘(108)在上游处连接,所述内部整流罩(102)包括通过上游紧固凸缘(118)紧固到所述进气道唇缘(108)的外表层(114),所述外表层(114)用于通过下游紧固凸缘(122)固定到外风扇外壳(116),所述进气道(1)包括至少一个独立的声学板(2),所述至少一个独立的声学板附接到所述外表层(114)并且包括穿孔的声学板(200)和蜂窝芯体(202)。


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    Title :

    NACELLE AIR INTAKE WITH ACOUSTIC PANEL


    Additional title:

    具有声学板的机舱进气道



    Publication date :

    2021-12-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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