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

A technology for air intake pipes and aircraft, applied in jet propulsion devices, gas turbine devices, air transportation, etc., can solve the problems of noise ineffectiveness, achieve the effect of improving comfort and avoiding the generation of sound waves

Pending Publication Date: 2021-09-24
SAFRAN NASEL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] By the way, patent application US5257498 discloses a curved guide grille for the discharge of hot air, but it has no effect on the noise

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

Examples

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Embodiment Construction

[0075] 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, rotating about the axis X to accelerate an air flow F upstream to downstream . 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 towards 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 partition 25 so as to define an annular cavity 204 known to those skilled in the art as a "D...

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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 comprising an inner wall facing the axis X and an outer wall for guiding an external air flow EXT, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow FAC into the inner cavity and at least one ventilation orifice (3) formed in the outer wall to allow the hot air flow FAC to escape after heating the inner cavity, the ventilation orifice (3) comprising an upstream edge (31), the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge (32), the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.

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 the aircraft to be propelled 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 in order 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 e...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/047F02C7/045
CPCF02C7/047F02C7/045Y02T50/60F05D2220/323F05D2250/38F05D2250/75F05D2260/2212F05D2260/232F05D2260/605F05D2260/96
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