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Fuel metering unit for aircraft engine

A fuel metering and engine technology, applied in the direction of engine components, machine/engine, engine control, etc., can solve the problems of damage quality and installation cost, undisclosed distinction detection strategy, non-existent solution, etc., to promote certification strategy, limit Effects of cost and physical impact

Pending Publication Date: 2021-07-23
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0017] The publication does not disclose a detection strategy that would allow the distinction of overheating that is not related to ignition actuation
[0018] On the other hand, the solution of this published text does not allow to ensure a sufficient thermal margin to ensure a "total failure" of the control computer, taking into account thermal inertia
[0019] Therefore, considering the state of the art, for a fuel supply control system with an overspeed protection function for an aircraft engine, without compromising quality and installation costs, and allowing compliance with certification limits to regulate degraded operating modes of the engine (for example in response to a fire situation) , there is no very satisfactory solution

Method used

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  • Fuel metering unit for aircraft engine
  • Fuel metering unit for aircraft engine
  • Fuel metering unit for aircraft engine

Examples

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no. 1 example

[0056] Figure 1A A control and protection system 100 for an aircraft engine implemented by a distributed architecture according to a first embodiment is shown.

[0057] Thus, the system 100 includes an engine control computer 110 that generates a flow rate set point C101 for the mass of fuel to provide the thrust required by the aircraft in real time.

[0058] Then, this set value C101 is transmitted to the electro-hydraulic mechanical metering unit 120 which performs fuel metering.

[0059] More precisely, the setpoint C101 is transmitted to the power control computer 123 of the electro-hydraulic mechanical metering unit 120 .

[0060] The control computer 123 determines a theoretical position setpoint Cth of the fuel metering member 125 (for example of the FMV type) of the electro-hydraulic mechanical metering unit 120 from the flow rate setpoint C101.

[0061] Based on the movement setpoint Cth, the control computer 123 transmits the electrical control setpoint C102 to th...

no. 2 example

[0091] Figure 1B A subsystem 200 for controlling the control and protection system 100 according to the second embodiment is shown.

[0092] The hydraulic servo valve 121 and actuator 122 (FMV) and its position sensor are located in the electronic fuel metering unit 120 .

[0093]However, unlike the first embodiment, some of the functions associated with fuel metering are implemented in the engine control computer 110: generation of flow rate setpoints, corrector network, generation of position commands, and acquisition of at least one position sensor, the position The sensors provide information about the position of the movable slider of the FMV.

[0094] As in the first embodiment, the control and protection system 100 can also comprise a flow meter as described in the first embodiment.

[0095] The flow meter allows measuring the mass flow of fuel originating in the electro-hydraulic mechanical metering unit 120 . Unlike the first embodiment, this measurement is then t...

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Abstract

The present invention relates to a fuel metering unit (120) for an aircraft engine, comprising: a metering member (125) configured to receive a position control signal and to meter the feed of fuel to the engine depending on said position control; a cutting member (126) configured to cut the feed of fuel to the engine; and characterized in that the fuel metering unit (120) also has a computer (124) for protecting and cutting the engine, said protecting and cutting computer (124) being configured to detect an over-speeding state of the engine speed and in response to the detection of an over-speeding state, to transmit a cutting control signal to a cutting control member contained in the cutting member (126).

Description

technical field [0001] The present invention relates to the general field of aeronautics. [0002] More specifically, the invention relates to the field of fuel supply control systems for aircraft engines. The engine is, for example, a turbine, such as a turbojet. Background technique [0003] In a known manner, the control system of an aircraft engine comprises a main electronic computer in the form of a housing enclosing one or more electronic boards, which are assigned to provide different functions. [0004] In current engines, the engine control system is generally responsible for controlling the fuel metering unit, which corresponds to a hydromechanical block usually called FMU (“Fuel Metering Unit”). [0005] The hydromechanical blocks are provided with several common functions. The hydromechanical block provides the metering of the fuel, through the metering means, that is, the conversion of the required information on the flow rate of the fuel within the flow rat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C9/26F02C9/28F02C9/46
CPCF02C9/263F02C9/28F02C9/46F05D2270/021F05D2270/3032F05D2270/304Y02T50/60F02C7/22F05D2220/323F05D2240/35
Inventor 吉列尔莫·阿尔西德·奥古斯特·弗莱特阿诺德·伯纳德·克莱芒·托马斯·茹达雷夫
Owner SAFRAN AIRCRAFT ENGINES SAS