Turbojet engine nacelle

Abstract

The present invention relates to a turbojet engine nacelle including an air inlet (3) arranged upstream from the turbojet engine, a middle section for surrounding a turbojet engine fan and the housing (6) thereof, and a downstream section, the middle section being produced from at least one aerostructure (51) capable of ensuring the external aerodynamic continuity of the nacelle, characterized in that said aerostructure is rigidly and removably connected to at least one surrounding stationary structure.

Description

technical field

[0001] The invention relates to a turbojet nacelle comprising an intermediate section for surrounding a turbojet fan. technical background

[0002] The aircraft is propelled by a number of turbojet engines housed in a nacelle that also houses the components of the auxiliary actuating equipment related to its operation, which ensure the performance of various functions such as thrust when the turbojet engines are running or stopped reverse system.

[0003] More specifically, the nacelle usually has a structure comprising an air intake upstream of the engine, an intermediate section intended to surround the fan of the turbojet engine, a section intended to surround the combustion chamber of the turbojet engine and accommodate thrust reversal means downstream segment.

[0004] The fan of a turbojet engine basically comprises a rotating shaft supporting a plurality of blades. The blades are surrounded at their radial ends by the casing.

[0005] To enable acc...

Examples

Embodiment Construction

[0037] Since it is known and figure 1 As shown, the nacelle 1 of a twin-flow turbojet engine generally comprises an outer structure comprising an upstream section 3 forming an air intake, an intermediate section 5 and a downstream section 9, the inner walls of which are formed by the fan of the turbojet engine. Formed by casing 6 of 7, said downstream section 9 may incorporate thrust reversal means.

[0038] This nacelle 1 further comprises an internal structure 11 comprising a cowling 13 of a turbojet engine 15 .

[0039] The outer structure of said nacelle 1 together with the inner structure 11 defines an annular airflow flow path 17 generally designated as "cold air flow path", where the term "cool air flow" is used in relation to the engine 15 In terms of thermal airflow generated.

[0040] Said fan 7 essentially exists in a propeller comprising a plurality of blades 19 and is mounted rotatably on a fixed hub 21 connected to the fan housing 6 by means of a plurality of f...

technical field

[0001] The invention relates to a turbojet nacelle comprising an intermediate section for surrounding a turbojet fan. technical background

[0002] The aircraft is propelled by a number of turbojet engines housed in a nacelle that also houses the components of the auxiliary actuating equipment related to its operation, which ensure the performance of various functions such as thrust when the turbojet engines are running or stopped reverse system.

[0003] More specifically, the nacelle usually has a structure comprising an air intake upstream of the engine, an intermediate section intended to surround the fan of the turbojet engine, a section intended to surround the combustion chamber of the turbojet engine and accommodate thrust reversal means downstream segment.

[0004] The fan of a turbojet engine basically comprises a rotating shaft supporting a plurality of blades. The blades are surrounded at their radial ends by the casing.

[0005] To enable acc...

Examples

Embodiment Construction

[0037] Since it is known and figure 1 As shown, the nacelle 1 of a twin-flow turbojet engine generally comprises an outer structure comprising an upstream section 3 forming an air intake, an intermediate section 5 and a downstream section 9, the inner walls of which are formed by the fan of the turbojet engine. Formed by casing 6 of 7, said downstream section 9 may incorporate thrust reversal means.

[0038] This nacelle 1 further comprises an internal structure 11 comprising a cowling 13 of a turbojet engine 15 .

[0039] The outer structure of said nacelle 1 together with the inner structure 11 defines an annular airflow flow path 17 generally designated as "cold air flow path", where the term "cool air flow" is used in relation to the engine 15 In terms of thermal airflow generated.

[0040] Said fan 7 essentially exists in a propeller comprising a plurality of blades 19 and is mounted rotatably on a fixed hub 21 connected to the fan housing 6 by means of a plurality of f...

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