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Device for controlling an aircraft engine comprising two redundant control channels

A technology for controlling channels and engines, applied to machines/engines, aircraft power units, gas turbine units, etc., can solve problems such as engine stall, affecting engine shutdown rate, etc., to improve shutdown rate, achieve redundant availability, and increase reliability. awesome effect

Pending Publication Date: 2021-11-12
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If the remaining channel fails, which can be detected by the hardware self-test, it will eventually isolate itself and cause the engine to stall
Therefore, this type of behavior adversely affects the rate of engine shutdowns in flight

Method used

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  • Device for controlling an aircraft engine comprising two redundant control channels
  • Device for controlling an aircraft engine comprising two redundant control channels
  • Device for controlling an aircraft engine comprising two redundant control channels

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0035] figure 1 An example of an apparatus for controlling an engine according to an embodiment of the present invention is shown. Preferably, the engine is an engine of an aircraft, for example a turbine.

[0036] The control device includes two control channels: a first control channel V1 and a second control channel V2.

[0037] Each control channel V1, V2 makes it possible, according to the calculated command or set point C V1 、C V2 to drive at least one actuator ACT. In operation, only one of the two channels drives the actuator ACT. It is the active channel. The other channel is considered passive and can take over for the active channel if the active channel fails.

[0038] Each control channel V1 , V2 receives an input variable A, B to be measured and on the basis of this calculates a command to the actuator ACT. These parameters are, for example: temperature and the like.

[0039] exist figure 1 In the example shown, each channel receives two different quanti...

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PUM

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Abstract

The invention relates to an engine control device comprising a first control channel (V1) and a second control channel (V2), each control channel comprising a first sensor (CAV1, CAV2) and a second sensor (CBV2, CBV2), each configured to provide, respectively, a first measurement (A) and a second measurement (B) to each channel, each of the channels having an active or passive state defining an active channel (V1) or a passive channel (V2), the active channel (V1) being designed to control at least one actuator (ACT) of the engine while the passive channel (V2) is designed to take over for the active channel if the latter fails.

Description

technical field [0001] The invention relates to a control device for a turbojet aircraft engine. More specifically, the invention relates to means for implementing the calculation of a given redundancy based on measurements from sensors configured to measure engine parameters. Background technique [0002] Turbojet engines are usually equipped with control devices which also provide protection against events with dangerous or catastrophic consequences, such as engine overspeed situations. Thus, the same device fulfills both functions. [0003] Such control devices usually comprise two identical channels, which enable redundancy when acquiring parameters and calculating setpoints for controlling one or more actuators. [0004] Ideally, these channels are independent of each other, but they often exchange data in order to combine measurements. The purpose of the merging is to have both channels doing the same calculation at the same moment in order to ensure thermal redunda...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B9/03
CPCG05B9/03G05B2219/24184G05B2219/24182G05B2219/24175B64D31/00F02C7/00
Inventor 克利斯朵夫·皮埃尔·乔治·马丁塞巴斯蒂安·雅克·弗朗索瓦·米歇尔·苏利埃
Owner SAFRAN AIRCRAFT ENGINES SAS
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