Nacelle for an aircraft bypass turbojet engine

A technology of nacelle and turbojet, applied in the field of aircraft, can solve the problems of maintaining the weight of the nacelle, aerodynamic loss, no fast and reliable device, etc.

Inactive Publication Date: 2013-09-25
AIRCELLE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] Known is no fast and reliable device that allows adjustment of the injection section of the main airflow in the annular flow path, while maintaining the weight of the nacelle and with small aerodynamic losses

Method used

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  • Nacelle for an aircraft bypass turbojet engine
  • Nacelle for an aircraft bypass turbojet engine
  • Nacelle for an aircraft bypass turbojet engine

Examples

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Embodiment Construction

[0046] Such as figure 1As shown, the nacelle 1 according to the invention has a substantially tubular shape along the longitudinal axis Δ. The nacelle 1 of the invention comprises an upstream section 2 (with an air intake lip 13 forming the air intake 3 ), an intermediate section 4 (surrounding the fan 5 of the turbojet 6 ) and a downstream section 7 . The downstream section 7 comprises an inner fixed structure 8 (IFS) and an outer fixed structure 9 (OFS) surrounding the upstream part of the turbojet 6 and a movable cowl (not shown) including thrust reversal means.

[0047] IFS8 and OFS9 define an annular flow path 10 allowing the passage of the main air flow 12 penetrating from the air inlet 3 into the nacelle 1 of the invention.

[0048] The nacelle 1 of the invention thus comprises walls delimiting a space, such as an air intake 3 or an annular flow path 10 , into which the primary air flow 12 permeates, circulates and is injected.

[0049] The nacelle 1 of the invention ...

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Abstract

The invention relates to a nacelle for a turbojet engine, having a longitudinal axis and a rear section including an annular flow path comprising walls (110) defining a space (3, 10) through which a main air flow (12) passes. The nacelle includes at least one device (100) for modulating the cross-section of the space (3, 10), comprising: means (102) for injecting an auxiliary flow (104) of a gas, configured to vary the orientation and / or speed of the auxiliary flow (104); suction means (106) for drawing in at least part of the injected auxiliary flow (112); and an internal auxiliary flow (109) return area (108) in one or more walls (110), said area being configured to allow the circulation of said part of the injected auxiliary flow (104) and the drawn-in auxiliary flow (112).

Description

technical field [0001] The invention relates to a nacelle for a twin-flow turbojet engine of an aircraft, and to an aircraft containing such a nacelle. Background technique [0002] The aircraft is driven by a plurality of turbojet engines each housed in a nacelle which also houses a set of auxiliary drive equipment associated with its operation to ensure that the various Function. These auxiliary drive devices include in particular mechanical systems for driving thrust reversers. [0003] The nacelle generally has a tubular structure along a longitudinal axis comprising: an air inlet upstream of the turbojet engine, an intermediate section surrounding the turbojet fan, and downstream surrounding the turbojet combustion chamber and housing the thrust reverser means part. This tubular structure usually terminates in an injection nozzle, the outlet of which is located downstream of the turbojet engine. [0004] Modern engines are designed to accommodate a twin-flow turboje...

Claims

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Application Information

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Patent Type & AuthorityApplications(China)
IPC IPC(8): F02K1/30B64C21/02B64D33/02B64D33/04F02C7/04
CPCB64D33/02B64D2033/0226B64D2033/0286F02C7/042F02K1/30Y10T137/0536Y02T50/60F02C7/047B64D29/06B64D2033/0266B64D2033/0273
Inventor帕特里克·哥诺迪克劳伦·艾伯特·布林
OwnerAIRCELLE