Aeroplane Gas Turbine Engine Control Apparatus with Dual Channel Failure Level Comparison
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Solution Overview
Problem
Existing control apparatuses for aeroplane gas turbine engines are unable to continue engine control when both control channels fail, as they only propose stopping the engine in such scenarios.
Innovation Solution
A control apparatus with two redundant control channels that include failure level determiners, transmitters, receivers, and outputting units to compare and send command values from the control channel with the lower failure level to ensure continuous engine operation, even when both channels are abnormal.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If two redundant control channels are implemented, then reliability is improved, but device complexity increases
Solution Approach 1:
The control apparatus is divided into two independent control channels, each capable of autonomous operation. Each channel includes separate command value calculation units, failure level determiners, transmitters, and receivers, allowing the system to segment control functions and maintain operation even when one channel fails.
Solution Approach 2:
The failure level determiner proactively identifies and quantifies abnormalities in sensors and devices before they cause complete control failure. By determining failure levels in advance and comparing them between channels, the system can switch to a healthier channel preemptively, maintaining control reliability.
2Reliability
If both control channels are failed, then engine control continuity is lost, but stopping the engine causes loss of productivity
Solution Approach 1:
The system converts the harmful effect of dual channel failure into a beneficial outcome by using failure level comparison. When both channels detect abnormalities, the system compares their failure levels and selects the channel with the lower failure level to maintain control, thereby converting a potentially catastrophic failure scenario into a manageable condition that preserves engine operation.
Solution Approach 2:
The system changes the parameter of control channel selection from a binary normal/failed state to a continuous failure level spectrum. By quantifying abnormality degrees as numerical failure levels and comparing these parameters between channels, the system can make informed decisions to maintain control continuity even when both channels exhibit some degree of degradation.
3Measurement precision
If failure level determination and comparison mechanisms are added, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The failure level determiner in each control channel serves multiple functions: it monitors sensor abnormalities, evaluates device performance, quantifies failure degrees, and prepares comparison data. This multi-functional component improves measurement precision without requiring separate dedicated systems for each function, thereby limiting the increase in device complexity.
Data Source
AI summary
An apparatus for controlling an aeroplane gas turbine engine has various sensors and devices for operating the engine, and two control channels each calculating a command value for controlling operation of the engine based on signals outputted from the sensors. In each of the control channels, it is determined whether any of the sensors and devices is abnormal based on the signals to determine a failure level of the control channel concerned with a numerical value. The failure level is compared with that of the other control channel and based thereon, the command value calculated by the control channel of smaller failure level is sent to the devices. With this, even when both control channels are failed, the engine control can be continued with taking the failure level into account.