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Nacell for bypass engine with high bypass ratio

A technology of turbine engine and pod, applied in the direction of machine/engine, sustainable transportation, efficient propulsion technology, etc.

Inactive Publication Date: 2009-05-20
AIRCELLE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This results in a larger overall diameter for the pod, which is problematic due to the tendency of aircraft manufacturers to have to fit shorter landing gear to aircraft with less underwing clearance

Method used

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  • Nacell for bypass engine with high bypass ratio
  • Nacell for bypass engine with high bypass ratio
  • Nacell for bypass engine with high bypass ratio

Examples

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Embodiment Construction

[0031] Before describing the embodiments of the present invention in detail, it is important to emphasize that the present invention is not limited to any particular type of inverter. Although the reverser is shown in the form of a cascade reverser with a moving cowl that slides along rails, the invention is also capable of utilizing reversers of various designs - in particular clamshell doors Formal - very easy to implement.

[0032] figure 1 A pod 1 of a bypass turbine engine with a high bypass ratio according to the prior art is shown.

[0033] The nacelle 1 is intended to form a tubular casing for a bypass turbine engine (not shown) with a high bypass ratio, and to direct its air flow generated by the blades of a fan (not shown), mainly A flow of hot air flows through a combustion chamber (not shown) of the turbine engine and a flow of cold air flows around the periphery of the turbine engine.

[0034] The structure of the nacelle 1 comprises: a front part forming the a...

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PUM

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Abstract

This invention relates to a nacelle for bypass engine with a high bypass ratio comprising an interior flow channel for a secondary flow generated by the bypass engine and having an external structure provided with a reverse thrust device capable of alternately shifting from a closed position in which it enables circulation of the direct-jet secondary flow inside the interior channel, to an open position in which it uncovers an opening in the external structure so as to enable reorientation of the secondary flow in an angled flow via activation of the reverse thrust means; in open position, the reverse thrust device partially blocks the interior channel so as to provide a leakage section therein, enabling circulation of a controlled leakage flow, said nacelle being characterized in that, when the thrust reversal device is in open position and has an angled-jet reversal section and a leakage section through the interior channel the sum of which is substantially equal to a direct-jet secondary flow discharge section, when the thrust reversal device is in closed position.

Description

technical field [0001] The invention relates to a nacelle for a bypass turbine engine with a high bypass ratio, comprising an internal flow channel through which the secondary flow generated by the turbine engine flows, and said internal channel has a thrust reverser The external structure of the device. Background technique [0002] Aircraft are propelled by a number of turbine engines housed in nacelles which also include a number of auxiliary actuating devices associated with their operation and performing various functions when the turbine engines are running or not. In particular, these auxiliary actuation means include mechanical systems for actuating thrust reversers. [0003] The pod typically has a tubular structure comprising: an air inlet upstream of the turbine engine; a middle section intended to surround the turbine engine fan; a downstream section housing the thrust reverser arrangement and intended to surround the turbine engine's combustion chamber, and usu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/72F02K1/70
CPCF02K1/72F02K1/70Y02T50/671Y02T50/60
Inventor 盖伊·贝纳德·沃谢尔让·法布里斯·马塞尔·波塔尔洛朗·阿尔贝·布林克里斯托弗·托雷尔
Owner AIRCELLE
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