초록 ▼

The invention relates to an improvement to an installation for preventing the ingress of super-cooled water, ice, snow and other debris as taught in U.S. Pat. No. 3,329,377. In the patent, an inertial separator effect is used to prevent ingress of super cooled water, ice, snow and other debris to an

The invention relates to an improvement to an installation for preventing the ingress of super-cooled water, ice, snow and other debris as taught in U.S. Pat. No. 3,329,377. In the patent, an inertial separator effect is used to prevent ingress of super cooled water, ice, snow and other debris to an aircraft engine. The effect is obtained by an installation including a duct formed in a sub-nacelle of the engine to extend generally longitudinally of the engine. An air deflecting surface in the duct confines the incoming air to a passage of reduced cross section, and an opening in the duct wall downstream of the deflecting surface is formed between the trailing edge of the deflecting surface and the leading edge of a rearward portion of the duct, the opening in the duct wall communicating with the engine air intake. In accordance with the present invention, any or all of the following improvements are made to the above installation: A. A CYCLIC ICE SHEDDER IS PROVIDED TO EXTEND INWARDLY FROM THE LEADING EDGE OF THE REARWARD PORTION; B. THE REARWARD PORTION IS FORMED IN THE SHAPE OF A HOPPER WHICH IS SPACED FROM THE OUTLET PASSAGE; C. A FAIRING IS PROVIDED AT THE TRAILING EDGE OF THE DEFLECTING SURFACE; AND D. A LOWER SURFACE OF THE DUCT IS CONTOURED BETWEEN THE TRAILING EDGE OF THE DEFLECTING SURFACE AND THE DISCHARGE OPENING OF THE DUCT TO PROVIDE A FAIRING BETWEEN THE CROSS SECTIONAL AREA OF THE DUCT AT THE TRAILING EDGE OF THE DEFLECTING SURFACE AND THE CROSS SECTIONAL AREA AT THE DISCHARGE OPENING.

대표청구항 ▼

For an aircraft engine comprising an encasing nacelle and provided with an air intake and an installation for reducing ingress of super-cooled water, ice, snow and other debris to said air intake, said installation comprising a duct extending generally longitudinally of said engine, an open inlet at

For an aircraft engine comprising an encasing nacelle and provided with an air intake and an installation for reducing ingress of super-cooled water, ice, snow and other debris to said air intake, said installation comprising a duct extending generally longitudinally of said engine, an open inlet at the forward end of said duct and an outlet, spaced from said inlet in the downstream direction of said duct, one of the walls of said duct being co-incident with a portion of said nacelle, an air deflecting surface in said duct extending rearwardly from said portion of said nacelle and in a direction away from said portion of said nacElle, the air deflecting surface extending over a part of the cross-section of said duct so as to confine incoming air to a passage of reduced cross-section, an opening in said portion of said nacelle downstream of the deflecting surface and formed between the trailing edge of the deflecting surface and the leading edge of a rearward part of said portion of said nacelle, said opening communicating with said air intake whereby air passing to said intake is deflected through a substantial angle around said deflecting surface whereas remaining air together with material of greater inertia passes without deflection to said opening through an outlet passage, one surface of said outlet passage being formed by said rearward part of said portion of said nacelle, the improvement comprising cyclic ice shedder means extending outwardly from and at right angles to said leading edge of said rearward part of said portion of said nacelle.