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Thrust reverser cascade including acoustic treatment

A turbine engine and diaphragm technology, which is applied in jet propulsion, high-efficiency propulsion technology, climate sustainability, etc., can solve problems that cannot be treated with turbine engine acoustic wave acoustics

Active Publication Date: 2021-12-17
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In particular, in the prior art, the volumes they use in the nacelle cannot be used for the acoustic treatment of the sound waves emitted by the turbine engine

Method used

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  • Thrust reverser cascade including acoustic treatment
  • Thrust reverser cascade including acoustic treatment
  • Thrust reverser cascade including acoustic treatment

Examples

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Embodiment Construction

[0049] image 3 with Figure 4 A first schematic sectional view and a second schematic sectional view respectively represent a thrust reverser cascade for an aircraft turbine engine according to an embodiment of the present invention.

[0050] The turbine engine includes a thrust reverser which may operate as described in Figures 1A and 1B or as described in Figures 2A and 2B.

[0051] The thrust reverser comprises a plurality of cascades 80 assembled into a mesh crown. Each cascade 80 includes a frame 81 in which a first partition 82 extends in a first direction and a second partition 83 extends in a second direction orthogonal to the first direction. The frame 81 and the first and second partitions 82 and 83 have a height H between 10 mm and 300 mm in a third direction orthogonal to the first and second directions.

[0052] The height of the second diaphragm 83 may be between 0.5 mm and 5 mm so as to be thick enough to withstand the load conditions it is subjected to but a...

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Abstract

The present invention relates to a cascade (80) for a thrust reversal device intended to be mounted on a turbomachine of an aircraft. The cascade (80) comprises first partitions (82) extending in a first direction (DA) and second partitions (83) extending in a second direction (DC) orthogonal to the first direction (DC), the second partitions (83) extend in a third direction (DR) secant to a plane comprising first and second directions (DA and DC) between first and second ends (85 and 86). Each second partition (83) forms, with reference planes (Pr) parallel to the second direction (DC) and to the third direction (DR), a plurality of different angles (alpha 1 to alpha 4) at separate positions (H1 to H4) of the height (H) of the second partitions (83) separating the first end (85) from the second end (86) of the second partitions (83), each angle (alpha 1 to alpha 4) being formed between a reference plane (Pr) and the tangent to the second partition (83) taken at the intersection between said corresponding reference plane (Pr) and the second partition (83) at the corresponding position (H1 to H4) of the height (H) of the second partition (83).

Description

technical field [0001] The present invention relates to the acoustic treatment of sound waves emitted by aircraft turbine engines, in particular at the turbine engine thrust reverser. Background technique [0002] When the turbine engine is running, the interaction between the airflow and the solid parts of the turbine engine is responsible for the noise that propagates through the turbine engine. [0003] One of the ways to attenuate this acoustic radiation is to integrate acoustic treatments on the surfaces that come into contact with the acoustic waves. [0004] Traditionally, the acoustic treatment of turbojet engines, and more specifically of the noise radiated by the interaction between the rotor and its environment, has been carried out using sound-absorbing panels arranged on the wetted surfaces of the ducts through which the sound waves travel. Wetted surfaces are surfaces that come into contact with fluid flow. These panels are usually sandwich-type composites, s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/72F02K1/82
CPCF02K1/72F02K1/827F05D2250/71F05D2240/129Y02T50/60F05D2220/323F05D2260/96B64D33/06F02C7/24
Inventor 诺曼·布鲁诺·安德烈·乔德杰雷米·保罗·弗朗西斯科·冈萨雷斯
Owner SAFRAN AIRCRAFT ENGINES SAS
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