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Aircraft engine monitoring process

An aircraft engine and engine technology, applied in the direction of engine testing, measuring devices, testing/monitoring control systems, etc.

Active Publication Date: 2008-08-06
HISPANO SUIZA SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this technique requires the determination of the most important parameters in the defect mode, the wear thresholds to be applied to these parameters and the influence of usage conditions on their characteristics

Method used

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  • Aircraft engine monitoring process

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Embodiment Construction

[0025] With reference to Figures 1 and 2, the illustrated architecture takes a four-engine aircraft as an example to give a detailed description. The monitoring and control system 10 of the engines m1, m2, m3, and m4 of the aircraft (not shown in the figure) is composed of FADEC computers 1, 2, 3, 4. Each computer monitors and controls the designated engine m(1), m(2), m(3), m(4), or, as shown in the figure, m1, m2, m3, m4.

[0026] FADEC, here are 4 units, which are connected to each other via an aircraft through the AFDX (Aviation Electronic Equipment Full Duplex) digital communication network. This digital communication network can be determined, for example, according to the ARINC (Aviation Radio Company) standard. A dedicated link for communication as described below, or through an existing link dedicated to other communications on the aircraft, to send data and parameters from the engine that it monitors and controls. FADEC is a two-way computer, which can enhance the inform...

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PUM

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Abstract

The method involves ordering and controlling aero-engines (ml-m4) by logic controllers (1-4), where the controllers are connected between the engines by an avionics full duplex (AFDX) digital communication network (5). Function parameters of the engines are monitored by the controller. Value of the parameters of the engine to be compared with value of the parameters that are emitted by the controllers is transmitted on the network. The engines are diagnosed under abnormal operation, if the difference between the two deviated values is higher than predetermined threshold.

Description

Technical field [0001] The present invention relates to a system capable of detecting the performance degradation of aircraft engines, in particular to the fact that all systems tested on the aircraft are equipped with at least two sets of equipment, and these systems are the main equipment of the aircraft, such as propeller devices, control systems and the like. Background technique [0002] At present, most BITEs (so-called "in-machine test equipment": BITE) mainly include sensors that can collect working parameters or data, and these parameters have been digitized and tested through software, which are called predetermined thresholds or mathematical models. [0003] Here, each engine is controlled by a computer, abbreviated as "FADE C" (Full Authority Digital Engine Control). [0004] Each full-power digital engine control monitors the operating parameters of the engine it controls. Such engine parameters are compared with preset thresholds. For similar layouts of engines, the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00
CPCG05B23/0237
Inventor 亚历山大·奥斯陆斯约纳森·本尼塔奥利弗·马卡让-雷米·麦斯
Owner HISPANO SUIZA SA