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Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air

An air intake pipe and aircraft technology, which is applied to the combustion of the intake port of the power plant, the deicing device, the jet propulsion device, etc., can solve the problems of increasing the overall size and weight of the turbojet engine, avoid the generation of sound waves, and improve the comfort. Effect

Pending Publication Date: 2021-10-08
SAFRAN NASEL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In fact, adding the vent duct increases the overall size and weight of the turbojet engine, which is not ideal
In addition, the vent duct has the disadvantage of jetting hot air flow FAC near heat sensitive downstream areas such as those made of composite materials

Method used

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  • Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
  • Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
  • Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air

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Embodiment Construction

[0074] The following will refer to Figure 4 The invention is described, Figure 4 Shown is a turbojet engine 1 extending along an axis X and comprising a fan 11 mounted in a nacelle comprising a housing 12, the fan 11 rotating about the axis X to induce flow F from upstream to downstream. accelerate. In the following, the terms "upstream" and "downstream" are defined in terms of the flow direction of the gas flow F. At its upstream end the nacelle comprises an intake duct 2 comprising an inner wall 21 facing the axis X and an outer wall 22 opposite the inner wall 21 passing through a leading edge 23 also called "intake rim" connect. Thus, the intake duct 2 allows separating the incoming airflow F into an internal airflow INT guided by the inner wall 21 and an external airflow EXT guided by the outer wall 22 . The inner wall 21 and the outer wall 22 are connected by a leading edge 23 and an inner septum 25 so as to define an annular cavity 204 known to those skilled in the...

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Abstract

The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall (21), which faces the axis X in order to guide an inner air flow INT, and an outer wall (22), which is opposite the inner wall (21), for guiding an external air flow EXT, the walls (21, 22) being connected by a leading edge (23) and an inner partition (25) so as to delimit an annular cavity (24). The air intake comprises means for injecting at least one hot air flow FAC into the inner cavity (24) and at least one ventilation orifice (3) formed in the outer wall (22) in order to allow the hot air flow FAC to escape after heating the internal cavity (24), the air intake comprising at least one disruption member (4) of the external air flow EXT, positioned upstream of the ventilation orifice (3), which extends outwardly from the outer wall (22).

Description

technical field [0001] The invention relates to the field of aircraft turbojet engines, and more particularly to an air intake duct of an aircraft turbojet engine nacelle including a deicing device. Background technique [0002] In a known manner, an aircraft comprises one or more turbojet engines to allow propelling the aircraft by accelerating the airflow flowing from upstream to downstream in the turbojet engines. [0003] refer to figure 1 , shows a turbojet engine 100 extending along an axis X and comprising a fan 101 mounted in a nacelle comprising a casing 102 and rotating about the axis X to accelerate the flow F from upstream to downstream. In the following, the terms "upstream" and "downstream" are defined in terms of the flow direction of the gas flow F. The nacelle comprises at its upstream end an intake duct 200 comprising an inner wall 201 oriented towards the axis X and an outer wall 202 opposite the inner wall 201 passing through a leading edge 203 also cal...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/047B64D15/04F02C7/045
CPCF02C7/047B64D2033/0233F05D2240/127F02C7/045F05D2260/14F05D2260/96B64D33/02B64D29/00B64D15/04Y02T50/60
Inventor 塞巴斯蒂安·劳伦特·玛丽·帕斯卡让-米歇尔·保罗·欧内斯特·诺格斯马克·凡赛伊夫弗朗索瓦·肖沃
Owner SAFRAN NASEL