Engine vibration and engine trim balance test system, apparatus and method

An engine and vibration velocity technology, applied in the simulation field of aircraft engine test, can solve problems such as manual calculation

Active Publication Date: 2014-01-01
THE BOEING CO
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  • Application Information

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Problems solved by technology

However, disadvantages of this method include the need to manually calculate each test condition and the fact that one signal can be generated at a time, which limits the evaluation of only one vibration type at a time

Method used

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  • Engine vibration and engine trim balance test system, apparatus and method
  • Engine vibration and engine trim balance test system, apparatus and method
  • Engine vibration and engine trim balance test system, apparatus and method

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Embodiment Construction

[0015] The following detailed description aims to provide a system of maximum capability that allows aircraft-level integration of test line replaceable units (LRUs) that monitor engine vibration. Typical LRUs with this capability include an Airborne Vibration Monitor (AVM) installed within the aircraft's avionics, an Engine Monitoring Unit (EMU) mounted on the engine, and a Health and Usage Monitoring System (HUMS) in the propeller aircraft , but the LRU list is not exhaustive, and alternative semantics exist. The design of the system can be applied or adapted to similar LRUs installed on other engines / aircraft types / propeller aircraft. Aircraft-level integration testing focuses on verification and validation of engine indication displays, events, messages, and interaction with diagnostics and predictive maintenance operations related to engine vibration systems. The LRU measures vibrations in the aircraft engine 12 using accelerometers. refer to figure 1 and figure 2 , ...

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Abstract

The present disclosure is generally directed to a simulated aircraft engine (12) accelerometer apparatus, system and method that that generates aircraft engine (12) simulator outputs. An accelerometer signal simulator (320) receives aircraft engine (12) simulator outputs and generates accelerometer signal simulator (320) outputs, and an accelerometer waveform generator (350) receives the accelerometer signal simulator (320) outputs and synchronizes at least one accelerometer signal simulator (320) outputs to a reference timing signal from one of the aircraft engine (12) simulator outputs. The simulated accelerometer (300) further includes a filter section (372, 374, 376 and 378) that receives and filters noise from the plurality of accelerometer waveform generator (350) outputs to generate a plurality of filtered accelerometer waveform generator (350) outputs, a mixer (380) that receives and combines each of the plurality of filtered accelerometer waveform generator (350) outputs to generate a single filtered accelerometer waveform generator (350) output, and a charge converter (382) that receives and converts the single filtered accelerometer waveform generator (350) output to a current charge vibration simulation output.

Description

technical field [0001] The general field of embodiments presented herein relates to simulation of aircraft engine testing, and more specifically, to systems, methods, and apparatus for multi-accelerometer simulation of aircraft engine and engine component testing. Background technique [0002] Existing solutions for aircraft engine testing include testing flight test aircraft by adding or removing counterweights to or from the fans and low pressure turbines. The disadvantages of this testing method are that it is expensive to run because it requires fuel to be burned during the test, the method requires extra time to add and remove weights, and the method introduces the possibility of damage to the engine and the flight test vehicle. Another method involves converting a signal generated using a signal generator to measure the vibration of a line replaceable unit (LRU). However, disadvantages of this method include the need to manually calculate each test condition and the f...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00
CPCG01M15/12B01D35/1435G01M15/02G01M7/022G01H1/003G01M7/00G06F30/17
Inventor R·B·施瓦布J·D·凯丽曼G·范
Owner THE BOEING CO
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