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Blade separator and engine containment test device

A separation device and blade technology, which is applied in the field of aero-engines, can solve the problems of low test success rate, time-consuming and labor-consuming, difficult to control accurately, etc., and achieve the effect of high test success rate and low test success rate

Active Publication Date: 2014-05-21
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
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Problems solved by technology

[0010] The purpose of the present invention is to propose a blade separation device and an engine containment test device equipped with the blade separation device, which solves the technical problems of low test success rate, time-consuming and labor-consuming in the prior art
In addition, the preferred technical solution of the present invention also solves the technical problem in the prior art that it is difficult to precisely control

Method used

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  • Blade separator and engine containment test device
  • Blade separator and engine containment test device
  • Blade separator and engine containment test device

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Embodiment Construction

[0033] Below through the accompanying drawings Figure 2 to Figure 5 And by way of listing some optional embodiments of the present invention, the technical solution (including the preferred technical solution) of the present invention is further described in detail. It should be noted that: any technical feature and any technical solution in this embodiment are one or more of a variety of optional technical features or optional technical solutions. All the alternative technical features and alternative technical solutions of the present invention are cited, and it is not convenient for the implementation of each technical feature to emphasize that it is one of the optional multiple implementation modes, so those skilled in the art should know: Any technical features and any technical solutions in the embodiments do not limit the protection scope of the present invention, and the protection scope of the present invention should include any alternative technical solutions that ...

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Abstract

The invention discloses a blade separator and an engine containment test device, relates to the aero-engine technology field and solves technical problems of a low test success rate and time / effort consuming existing in the prior art. The blade separator comprises an explosive, a storage chamber and a control device, wherein the storage chamber is arranged at a blade tenon outer wall or a groove inner wall of a wheel disc, the explosive is embedded in the storage chamber, and the control device is used for detonating the explosive to separate a blade into at least two parts through explosion of the explosive. The engine containment test device comprises the blade separator. The blade separator and the engine containment test device are used for improving a success rate of containment tests.

Description

technical field [0001] The invention relates to the technical field of aeroengines, in particular to a blade separation device and an engine containment test device provided with the blade separation device. Background technique [0002] The aero-engine blade inclusive test is one of the important tests that must be carried out when the engine type is finalized or airworthiness certification is obtained. This test is used to judge whether the aero-engine meets the inclusive requirements after the blade falls off. Containment refers to the containment performance of the engine structure to the debris formed after the blade is generated. A well-contained engine is more resistant to debris penetration. [0003] When carrying out the blade containment test, certain test conditions need to be met, and the test conditions include: [0004] 1. If the blade breaks at the most dangerous position, you can choose to break at the outermost tongue and groove of the blade, or 80% of a s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/02G01M15/00
Inventor 陈健侯乃先杨坤周超羡
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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