Removable air intake structure for turbojet engine nacelle

Removable air intake structure for turbojet engine nacelle

  • CN 101,523,030 A
  • Filed: 10/02/2007
  • Published: 09/02/2009
  • Est. Priority Date: 10/02/2006
  • Status: Active Application
First Claim
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1. engine compartment (1) that is used for turbojet engine, comprise the described turbojet engine that air-flow can be led fan air intake structure (4) and be designed for the central structure (5) that surrounds described fan, described air intake structure is connected to described central structure so that aerodynamic continuity to be provided, described central structure comprises the housing (9) that is designed for the described fan of encirclement on the one hand, comprise external structure (13) on the other hand, described engine compartment is characterised in that, described air intake structure comprise on the one hand by described housing be connected to described central structure and with at least one wainscot (41) of the fixed structure of the described engine compartment of its formation, comprise on the other hand in removable mode and be connected to described fixed structure and be combined with at least one outer vertically panel (40) of air inlet antelabium (4a), described outer panels is removable between running position and maintenance position, wherein in described running position, described outer panels provides the aerodynamic continuity with the external structure of described middle part part, and described air inlet antelabium provides the aerodynamic continuity with the described wainscot of described air intake structure, at described maintenance position, described outer panels is separated from the described external structure of described middle part part, and described air inlet antelabium is from the described wainscot separation of described air intake structure.

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