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Aircraft propulsion system

A propulsion system and aircraft technology, applied to aircraft parts, aircraft power units, aircraft power unit components, etc., can solve the problems of increasing the radial size of the engine compartment, difficulty in inserting turbojet engines, and increasing resistance

Active Publication Date: 2011-05-25
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] Therefore, for a given bypass ratio, it is required to increase the radial dimension of the nacelle, thereby increasing the drag, and it is difficult to incorporate a turbojet with a large bypass ratio

Method used

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Examples

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Embodiment Construction

[0046] figure 1 and figure 2 The illustrated aircraft propulsion system 10 includes a generally cylindrical nacelle 12 within which is mounted a bypass turbojet engine 14 suspended from a bracket 16 secured to the wing of the aircraft. below.

[0047] On the front side, the motor 14 has a fan wheel driven in rotation within a fan housing 18 whose downstream end is connected to the outer cylindrical wall 20 of the intermediate housing.

[0048] The nacelle 12 includes, from its upstream end, a semi-cylindrical fairer plate 22 (sometimes referred to as an intake sleeve) and a semi-cylindrical fairer plate 24 which surround the outer walls of the fan housing 18 and the intermediate housing. 20, and includes an outer casing 26 (sometimes referred to as an outer fixed structure (OFS, Outer Fixed Structure)) at the downstream end, the outer casing 26 is composed of two semi-cylindrical shells 28, which are fastened to the middle shell The outer wall 20 and optionally includes th...

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PUM

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Abstract

The invention provides an aircraft propulsion system (10) comprising a bypass turbojet engine which is surrounded by a nacelle, and means (80) of attaching the engine to a pylon (16) of an aircraft, the nacelle (12) comprising an internal structure exhibiting symmetry of revolution with a rigid framework formed of an upstream annular frame (50) attached to an intermediate casing (38) of the engine, of a downstream annular frame (52) supporting the exhaust casing (40) of the engine, and of longitudinal arms (54, 56, 58, 60) connecting these frames (50, 52), the downstream annular frame (52) being fixed to the pylon (16) by resilient or articulated suspension means.

Description

technical field [0001] The invention relates to an aircraft propulsion system comprising a bypass turbojet engine having at least a compressor, a combustion chamber, a turbine and a fan mounted upstream of the compressor and driven in rotation by the turbine, the engine being composed of The nacelle encloses, and the nacelle, downstream of the fan, defines an annular flow section for the secondary air flow around the casing of the compressor, combustion chamber and turbine, which provides the main part of the thrust. Background technique [0002] The propulsion system is attached to a structural member of the aircraft, such as an aircraft wing, so that the propulsion system can transmit the forces generated by the engine during various operating phases to the structural member. [0003] The turbojet engines of modern civil aircraft are characterized by high bypass ratios, ie the ratio of secondary flow to primary flow is greater than 5 and can be as high as 9 or 10, especial...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/26B64D27/40
CPCB64D27/26Y02T50/44B64D2027/264B64D29/00B64D2027/266Y02T50/40B64D27/402B64D27/404B64D27/40
Inventor 沃特·鲍克安妮-罗尔·玛丽·克莱门斯·德加勒
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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