A control method and device for preventing continuous misjudgment of surge in an aircraft engine

Abstract

The present application belongs to the field of engine control technology, and specifically relates to a control method and device for preventing continuous misjudgment of surge in aircraft engines. The method includes step S1, continuously monitoring whether the engine gives a surge signal, and if a surge signal is received from the engine, starting a timer for timing; step S2, continuously monitoring the engine exhaust temperature; step S3, when the timing time given by the timer is greater than the set value, and the engine exhaust temperature is lower than the temperature threshold, shielding the anti-surge control of the engine controller; step S4, when the surge signal is disconnected, or the engine exhaust temperature is higher than the temperature threshold, releasing the anti-surge control of the engine controller. The present application avoids the problem of insufficient engine thrust in the air caused by continuous anti-surge; at the same time, it can ensure that the engine controller re-executes anti-surge and exits surge in the event of real surge, thereby reducing the user's use risk.

Description

Technical Field

[0001] The present application belongs to the field of engine control technology, and specifically relates to a control method and device for preventing continuous misjudgment of surge in an aircraft engine. Background Art

[0002] Generally, in order to identify the occurrence of aircraft engine surge, a surge annunciator is used for judgment. However, since the surge annunciator itself and the detection circuit itself cannot be tested, there is a probability of continuous misjudgment of surge occurrence.

[0003] Currently, using surge signals to detect aircraft engine surge can accurately identify true surge, but there are also issues with persistent misjudgments of surge due to sensor failure or detection circuit malfunction. When surge is persistently misjudged, the engine controller continuously cuts fuel to eliminate surge, causing a continuous decrease in engine thrust and making it impossible to maintain flight performance. This poses operational risks and, in severe cases, can result in aircraft crashes and fatalities. Summary of the Invention

[0004] To address one of the aforementioned issues, this application provides a control method and device for preventing persistent misjudgment of surge in an aircraft engine. This method allows for the most accurate identification of the fault mode in which a surge annunciator persistently misjudgments surge, enabling appropriate remedial measures to be taken to prevent a sustained reduction in engine thrust. Furthermore, when a fault mode is misidentified, the occurrence of actual surge can be determined by abnormal changes in relevant parameters, allowing appropriate remedial measures to be taken.

[0005] In a first aspect, the present application provides a control method for preventing continuous misjudgment of surge in an aircraft engine, mainly comprising:

[0006] Step S1: continuously monitoring whether the engine gives a surge signal, and if the engine gives a surge signal, starting a timer to count;

[0007] Step S2, continuously monitoring the engine exhaust temperature;

[0008] Step S3: when the timing time given by the timer is greater than the set value and the engine exhaust temperature is lower than the temperature threshold, shielding the anti-gasping control of the engine controller;

[0009] Step S4: when the surge signal is disconnected or the engine exhaust temperature is higher than a temperature threshold, releasing the anti-surge control of the engine controller.

[0010] Preferably, before step S3, the method further includes determining the temperature threshold, and determining the temperature threshold includes:

[0011] Get the maximum exhaust temperature of the current engine at idle state;

[0012] On the basis of the maximum exhaust temperature, a set temperature difference is added to form the temperature threshold.

[0013] Preferably, the set temperature difference is any value within the range of 10 to 50°C.

[0014] A second aspect of the present application provides a control device for preventing continuous misjudgment of surge in an aircraft engine, mainly comprising:

[0015] The surge signal monitoring module is used to continuously monitor whether the engine has given a surge signal. If a surge signal is received from the engine, a timer is started to count.

[0016] Exhaust temperature monitoring module, used to continuously monitor engine exhaust temperature;

[0017] a gas relief control shielding module, configured to shield the gas relief control of the engine controller when the timing time given by the timer is greater than a set value and the engine exhaust temperature is lower than a temperature threshold;

[0018] The anti-surge control release module is used to release the anti-surge control of the engine controller when the surge signal is disconnected or the engine exhaust temperature is higher than a temperature threshold.

[0019] Preferably, the control device further includes a temperature threshold setting module for determining the temperature threshold, and the temperature threshold setting module includes:

[0020] The exhaust temperature maximum value acquisition unit is used to obtain the maximum exhaust temperature of the current engine in the idling state;

[0021] The temperature threshold generating unit is used to add a set temperature difference value to the maximum exhaust temperature to form the temperature threshold value.

[0022] Preferably, the set temperature difference is any value within the range of 10 to 50°C.

[0023] The key point of this application is how to effectively avoid the occurrence of real surge. Even if the controller makes a misjudgment, it can be identified through changes in relevant parameters and re-execute the surge relief.

[0024] This application can ensure that when the surge annunciator continuously falsely reports "surge", anti-surge control will no longer be executed, thus avoiding the problem of insufficient engine thrust in the air caused by continuous anti-surge; it can also ensure that when there is real surge, even if the controller makes a misjudgment, it can identify it through changes in relevant parameters, re-execute anti-surge, and exit surge, reducing the user's usage risk. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1This is a flow chart of a preferred embodiment of a control method for preventing continuous misjudgment of surge in an aircraft engine according to the present application. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and should not be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in conjunction with the drawings.

[0027] In a first aspect, the present application provides a control method for preventing continuous misjudgment of surge in an aircraft engine, mainly comprising:

[0028] Step S1: continuously monitoring whether the engine gives a surge signal, and if the engine gives a surge signal, starting a timer to count;

[0029] Step S2, continuously monitoring the engine exhaust temperature;

[0030] Step S3: when the timing time given by the timer is greater than the set value and the engine exhaust temperature is lower than the temperature threshold, shielding the anti-gasping control of the engine controller;

[0031] Step S4: when the surge signal is disconnected or the engine exhaust temperature is higher than a temperature threshold, releasing the anti-surge control of the engine controller.

[0032] Aircraft engine surge detectors have a failure mode where they can misjudge surge after a sensor failure or a faulty detection circuit. In this failure mode, the controller can detect surge signals that persist for a certain period of time. However, after an aircraft engine surges, there is also a mode where the surge signal persists, causing the controller to misjudge the surge detector or detection circuit failure, resulting in no surge action and potentially causing engine overheating or mechanical failure. Therefore, further identification of this "misjudgement" mode is necessary.

[0033] Typically, when an aircraft engine surges, the user will reduce the engine's status. However, when the engine actually surges, the exhaust temperature will rise rapidly, exceeding the specified value. However, when the engine is misjudged as a "surge annunciator or detection circuit failure," the exhaust temperature will be relatively low. Therefore, the aforementioned behavior can be used to identify whether the controller has made a "misjudgment," and if so, re-implement surge measures.

[0034] To this end, the present application uses step S3 to determine whether to execute the entry logic of shielding the anti-panting control of the present application. If the above two conditions are met at the same time, the engine controller will no longer perform anti-panting control. Then, the exit logic of the present application is set in step S4, that is, if any one of the above two conditions is met, the engine controller will no longer be supervised, and the engine controller will continue to determine whether anti-panting control is needed according to its own judgment logic.

[0035] In some optional implementations, step S3 further includes determining the temperature threshold, where determining the temperature threshold includes:

[0036] Get the maximum exhaust temperature of the current engine at idle state;

[0037] On the basis of the maximum exhaust temperature, a set temperature difference is added to form the temperature threshold.

[0038] In some optional embodiments, the set temperature difference is any value from 10 to 50°C.

[0039] A second aspect of the present application provides a control device for preventing continuous misjudgment of surge in an aircraft engine corresponding to the above method, mainly comprising:

[0040] The surge signal monitoring module is used to continuously monitor whether the engine has given a surge signal. If a surge signal is received from the engine, a timer is started to count.

[0041] Exhaust temperature monitoring module, used to continuously monitor engine exhaust temperature;

[0042] a gas relief control shielding module, configured to shield the gas relief control of the engine controller when the timing time given by the timer is greater than a set value and the engine exhaust temperature is lower than a temperature threshold;

[0043] The anti-surge control release module is used to release the anti-surge control of the engine controller when the surge signal is disconnected or the engine exhaust temperature is higher than a temperature threshold.

[0044] In some optional embodiments, the control device further includes a temperature threshold setting module for determining the temperature threshold, and the temperature threshold setting module includes:

[0045] The exhaust temperature maximum value acquisition unit is used to obtain the maximum exhaust temperature of the current engine in the idling state;

[0046] The temperature threshold generating unit is used to add a set temperature difference value to the maximum exhaust temperature to form the temperature threshold value.

[0047] In some optional embodiments, the set temperature difference is any value from 10 to 50°C.

[0048] This application can ensure that when the surge annunciator continuously falsely reports "surge", anti-surge control will no longer be executed, thus avoiding the problem of insufficient engine thrust in the air caused by continuous anti-surge; it can also ensure that when there is real surge, even if the controller makes a misjudgment, it can identify it through changes in relevant parameters, re-execute anti-surge, and exit surge, reducing the user's usage risk.

[0049] Although the present application has been described in detail above using general descriptions and specific embodiments, it will be apparent to those skilled in the art that modifications or improvements may be made based on the present application. Therefore, such modifications or improvements, which do not depart from the spirit of the present application, are within the scope of protection claimed in the present application.

Claims

1. A control method for preventing continuous misjudgment of surge in an aircraft engine, characterized in that: include: Step S1: continuously monitoring whether the engine gives a surge signal, and if the engine gives a surge signal, starting a timer to count; Step S2, continuously monitoring the engine exhaust temperature; Step S3: when the timing time given by the timer is greater than the set value and the engine exhaust temperature is lower than the temperature threshold, shielding the anti-gasping control of the engine controller; Step S4: when the surge signal is disconnected or the engine exhaust temperature is higher than a temperature threshold, releasing the anti-surge control of the engine controller; Wherein, before step S3, the method further includes determining the temperature threshold, and determining the temperature threshold includes: Get the maximum exhaust temperature of the current engine at idle state; On the basis of the maximum exhaust temperature, a set temperature difference is added to form the temperature threshold; the set temperature difference is any value within the range of 10 to 50°C.

2. A control device for preventing continuous misjudgment of surge in an aircraft engine, characterized in that: include: The surge signal monitoring module is used to continuously monitor whether the engine has given a surge signal. If a surge signal is received from the engine, a timer is started to count. Exhaust temperature monitoring module, used to continuously monitor engine exhaust temperature; a gas relief control shielding module, configured to shield the gas relief control of the engine controller when the timing time given by the timer is greater than a set value and the engine exhaust temperature is lower than a temperature threshold; a surge control release module, configured to release the surge control of the engine controller when the surge signal is disconnected or the engine exhaust temperature is higher than a temperature threshold; The control device further includes a temperature threshold setting module for determining the temperature threshold, and the temperature threshold setting module includes: The exhaust temperature maximum value acquisition unit is used to obtain the maximum exhaust temperature of the current engine in the idling state; a temperature threshold generating unit, configured to add a set temperature difference value to the maximum exhaust temperature to form the temperature threshold; The set temperature difference is any value between 10 and 50°C.

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