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Self-mounted cascade for a thrust reverser

A thrust reverser and blade cascade technology, applied in jet propulsion devices, machines/engines, etc., can solve the problem of high cost and high cost

Inactive Publication Date: 2013-02-13
AIRCELLE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Ultimately, the cost of self-installing the cascade 51 assembly is higher than using a stand-alone cascade

Method used

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  • Self-mounted cascade for a thrust reverser
  • Self-mounted cascade for a thrust reverser
  • Self-mounted cascade for a thrust reverser

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0094] Figure 7 Figure 9 shows an assembly 61 of a self-installing cascade according to a first embodiment of the invention.

[0095] Each cascade 61 is provided with a plurality of cells and has two opposite through-hole front surfaces, in this example, in Figure 9a to Figure 9c The upper front surface 610 and the lower front surface 611 are visible in .

[0096] Each cascade 61 has an upstream portion 612 intended to be fastened to the front frame (not shown) and an opposite downstream portion 613 which is free, ie not fastened to the rear frame.

[0097] In addition, each cascade 61 has two opposite side edges extending along the entire width LA of said cascade 61, namely an upstream side edge 614 located in the upstream portion 612 and a downstream side edge 615 located in the downstream portion 613, said The side edges 614, 615 of the cascade 61 form the circumferential or peripheral edges of the cascade assembly 61 in the thrust reverser and extend in an arcuate mann...

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PUM

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Abstract

The invention relates to a self-mounted cascade (61) for a thrust reverser of an airplane jet engine nacelle, said cascade comprising an upstream portion (612), provided with an upstream attachment means designed for attaching the cascade onto a stationary structure of the nacelle, and moreover comprising an opposite downstream portion (613) on which downstream connection means (617, 620), placed only on said downstream portion and designed to connect the cascade to at least one adjacent cascade, are provided so that two adjacent cascades are directly connected to one another only in the respective downstream portions thereof by the downstream connection means thereof. Said downstream portion corresponds to an area extending from a downstream side edge over a length less than or equal to N times the length of the last cavity located along said downstream side edge, where N is less than 3. The present invention is of use in the field of airplane jet engine nacelles.

Description

technical field [0001] The invention relates to a self-installing cascade of thrust reversers for aircraft turbojet nacelles. [0002] The invention also relates to a cascade assembly and an aircraft turbojet nacelle comprising such an assembly. Background technique [0003] The aircraft operates by means of a number of turbojet engines housed in a nacelle which also houses a set of actuating means associated with its operation, which perform different functions when the turbojet engines are running or stopped. These associated actuating means include in particular mechanical thrust reverser systems. [0004] Such as figure 1 As shown, the nacelle generally has a tubular structure comprising an air intake 2 upstream of the turbojet engine, an intermediate structure 3 designed to surround the fan of the turbojet engine, housing thrust reverser means (also called thrust reverser ) and is designed to surround the downstream section 4 of the turbojet combustion chamber, and t...

Claims

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Application Information

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IPC IPC(8): F02K1/72
CPCF02K1/72F02K3/025
Inventor 居·伯纳德·沃琪尔
Owner AIRCELLE
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