Flameout prevention control method for aero-engine

Abstract

The invention belongs to the technical field of aero-engines, and particularly relates to an aero-engine flameout prevention control method which comprises the steps that S1, a specific working condition point where a current engine is located is recognized; s2, obtaining a threshold value in an anti-flameout database for judgment, and if the requirement is met, executing the next step; if the requirement is not met, the normal control algorithm logic is directly carried out until the actuator works and the operation is directly finished; s3, the threshold value is obtained for further learning to give an optimal control parameter, and the optimal control parameter is output to an actuator; and S4, the actuator performs control according to the optimal control parameters. By monitoring the state of the engine in real time and obtaining the optimal control parameters, the engine can stably operate under various working conditions, flameout of the engine is prevented, and the reliability, safety and convenient operability of the aero-engine are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation engines, and in particular to an aviation engine flameout prevention control method. Background Art

[0002] With the development of aviation technology, aircraft engines are attracting increasing attention. However, aircraft engines are prone to flameout under low temperature and low load conditions, which can pose a safety hazard. Aircraft engines have strict requirements for power, economy, and safety, and cannot simply adopt the control methods of automotive engines. Therefore, it is desirable to provide a more intelligent and precise aircraft engine flameout prevention control method, specifically to improve the reliability and safety of aircraft engines and make operation simpler and more convenient. Summary of the Invention

[0003] In order to make up for the deficiencies of the prior art and solve the problems existing in the prior art, the present invention proposes an aircraft engine flameout prevention control method.

[0004] The technical solution adopted by the present invention to solve the technical problem is: an aircraft engine flameout prevention control method according to the present invention comprises the following steps: S1: Identify the specific operating point of the current engine; S2: Obtain the threshold value in the anti-stall database for judgment. If the requirement is met, proceed to the next step; if not, directly follow the normal control algorithm logic and end the actuator work directly; S3: Obtain the threshold value for further learning to obtain the optimal control parameters, and output them to the actuator; S4: The actuator is controlled according to the optimal control parameters.

[0005] Preferably, in step S1, identifying the specific operating point of the current engine includes identifying the current atmospheric ambient temperature, atmospheric pressure, engine speed and the current engine intake temperature.

[0006] Preferably, a plurality of sensors are provided to monitor the engine operating status in real time, and the plurality of sensors feed back the collected data to the engine control system, and the plurality of sensors are connected to the engine control system.

[0007] Preferably, the engine control system includes an engine controller, which may be single or multiple, and the actuator is connected to the engine controller.

[0008] Preferably, the multiple sensors include an atmospheric temperature sensor, an atmospheric pressure sensor, an intake air temperature sensor, a rotation speed sensor, an exhaust temperature sensor, and the like.

[0009] Preferably, the multiple sensors are digital sensors.

[0010] Preferably, the method for forming the anti-stall database comprises the steps of: ① Acquisition of data at various engine operating points under different atmospheric pressures in the international standard atmosphere (ISA) environment; ② Based on the standard ISA ambient temperature under different atmospheric pressures, obtain data for all relevant ambient temperatures and corresponding engine operating points; ③ Based on steps ① and ②, control the engine in different environments to trigger various operating points corresponding to the intake air temperature, and obtain full coverage data; ④Summarize the data obtained in steps ①, ② and ③ to form a complete anti-stall database.

[0011] Preferably, in step S3, during the self-learning process, the anti-stall control algorithm will continuously update the decision model according to the feedback signal and gradually move towards the optimal solution.

[0012] Preferably, the feedback signal includes external environment changes and engine hardware loss parameters.

[0013] The present invention is beneficial in that: By real-time monitoring of engine status and obtaining optimal control parameters, the engine can be kept running stably under various operating conditions, preventing flameout and improving the reliability, safety and operability of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0015] Figure 1 This is a flowchart of an aircraft engine flameout prevention control method according to Example 1; Figure 2 This is a diagram showing the composition of the monitoring system of Example 1. DETAILED DESCRIPTION

[0016] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0017] Example 1 See also Figure 1 As shown, a method for preventing flameout of an aircraft engine is provided, the method comprising the following steps: S1: Identify the specific operating point of the current engine; S2: Obtain the threshold value in the anti-stall database for judgment. If the requirement is met, proceed to the next step; if not, directly follow the normal control algorithm logic and end the actuator work directly; S3: Obtain the threshold value for further learning to obtain the optimal control parameters, and output them to the actuator; S4: The actuator is controlled according to the optimal control parameters.

[0018] Specifically, the purpose of the present invention is to provide an anti-stall control method for an aircraft engine, which can achieve stable operation of the engine under various working conditions by real-time monitoring of the engine status and prevent the occurrence of stalling.

[0019] The control method of the present invention uses multiple sensors to measure the actual operating state of the engine, and uses a control algorithm to adjust the fuel injection amount to optimize the engine combustion state, thereby ensuring the stability and safety of engine operation control in various complex environments.

[0020] In the above step S1 , identifying the specific operating point of the current engine includes identifying the current atmospheric temperature, atmospheric pressure, engine speed, and the current engine intake temperature.

[0021] In the present invention, multiple sensors are set to monitor the engine operating status in real time, and the multiple sensors feed back the collected data to the engine control system. The multiple sensors are connected to the engine control system. Figure 2 As shown, the engine control system includes an engine controller, which can be single or multiple (with a higher safety factor), and the actuator is connected to the engine controller.

[0022] In the present invention, the multiple sensors include an atmospheric temperature sensor, an atmospheric pressure sensor, a rotational speed sensor, an intake air temperature sensor, and an exhaust temperature sensor. The atmospheric temperature sensor is used to collect the atmospheric temperature, the atmospheric pressure sensor is used to collect the atmospheric pressure, the rotational speed sensor is used to collect the engine speed, the intake air temperature sensor is used to collect the engine intake air temperature, and the exhaust temperature sensor is used to measure the temperature of the exhaust system.

[0023] The present invention utilizes a real-time monitoring system comprised of four main components: various sensors, an engine controller, an engine wiring harness, and an actuator. This system monitors the engine's operating status in real time and provides timely feedback to the engine control system. The engine controller uses this feedback to determine whether preset thresholds are met, adjusting various operating parameters to ensure stable engine operation under various conditions.

[0024] In this invention, high-precision digital sensors are used as sensors. When the controller is powered on, the real-time monitoring system automatically enters a self-check state to confirm that all sensors and control components are functioning properly. Once the engine starts running and enters operational mode, the engine controller collects, processes, and interprets the collected sensor signals, taking appropriate action to ensure the engine operates normally in any complex environment, ensuring safe and reliable flight.

[0025] While the engine is in the air, its impact is primarily determined by changes in intake air temperature, external environmental conditions (e.g., atmospheric temperature and pressure), and engine operating conditions. Throughout operation, the anti-stall control algorithm repeatedly assesses and checks the engine's operating environment and conditions.

[0026] In the above step S2, during the engine operation, the judgment method for the anti-stall control algorithm is mainly: During engine operation, the anti-stall control algorithm will judge the current atmospheric pressure, current atmospheric temperature, current intake temperature, and current engine operating conditions (including engine speed and load). If the preset thresholds are met, further optimization learning will be performed based on the thresholds, and the optimal control parameters will be given and output to the actuator to complete the work, ensuring safe and reliable operation of the engine.

[0027] In the present invention, the method for forming an anti-stall database includes the following steps: Relying on simulation and test simulation, the data acquisition of all operating points of the engine is completed: ① Under the International Standard Atmosphere (ISA) environment, obtain data at various operating points of the engine at different atmospheric pressures, especially data corresponding to the flameout condition that enables stable engine combustion; ② Based on the standard ISA ambient temperature under different atmospheric pressures, obtain the flameout boundary data of each engine operating point corresponding to all ambient temperatures involved; ③ Based on steps ① and ②, control the flameout boundaries of each operating point corresponding to the intake temperature that can be triggered by the engine in different environments, and obtain full coverage data.

[0028] ④According to the results of steps ①②③, summarize the data to form a complete anti-stall database.

[0029] In the above step S3, based on the complete anti-stall database, the anti-stall control algorithm performs a reinforcement learning method for each working condition, that is, through continuous trial and adjustment, to find the optimal control algorithm strategy.

[0030] In step S3, during the self-learning process, the anti-stall control algorithm continuously updates its decision-making model based on feedback signals such as changes in the external environment and engine hardware loss parameters, gradually approaching the optimal solution. This adapts to the complex and diverse operating conditions of the engine, ensuring the safety and reliability of the engine during flight.

[0031] Throughout this specification, references to terms such as "one embodiment," "example," or "specific example" indicate that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0032] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention, and such changes and modifications fall within the scope of the invention as claimed.

Claims

1. A method for preventing an aircraft engine from stalling, characterized in that: The following steps are involved: S1: Identify the specific operating point of the current engine; S2: Obtain the threshold value in the anti-stall database for judgment. If the requirement is met, proceed to the next step; if not, directly follow the normal control algorithm logic and end the actuator work directly; S3: Obtain the threshold value for further learning to obtain the optimal control parameters, and output them to the actuator; S4: The actuator is controlled according to the optimal control parameters.

2. The aircraft engine flameout prevention control method according to claim 1, characterized in that: In step S1, identifying the specific operating point of the current engine includes identifying the current atmospheric temperature, atmospheric pressure, engine speed, and the current engine intake temperature.

3. The aircraft engine flameout prevention control method according to claim 1, characterized in that: A plurality of sensors are provided to monitor the engine operating status in real time, and the plurality of sensors feed back the collected data to the engine control system, and the plurality of sensors are connected to the engine control system.

4. The aircraft engine flameout prevention control method according to claim 3, characterized in that: The engine control system includes an engine controller, which may be single or multiple. The actuator is connected to the engine controller.

5. The aircraft engine flameout prevention control method according to claim 4, characterized in that: The multiple sensors include an atmospheric temperature sensor, an atmospheric pressure sensor, an intake air temperature sensor, a rotation speed sensor, an exhaust temperature sensor, and the like.

6. The aircraft engine flameout prevention control method according to claim 4, characterized in that: The plurality of sensors are digital sensors.

7. An aircraft engine flameout prevention control method according to any one of claims 1 to 6, characterized in that: The method for forming the anti-stall database comprises the steps of: ① Acquisition of data at various engine operating points under different atmospheric pressures in the international standard atmosphere (ISA) environment; ② Based on the standard ISA ambient temperature under different atmospheric pressures, obtain data for all relevant ambient temperatures and corresponding engine operating points; ③ Based on steps ① and ②, control the engine in different environments to trigger various operating points corresponding to the intake air temperature, and obtain full coverage data; ④Summarize the data obtained in steps ①, ② and ③ to form a complete anti-stall database.

8. The aircraft engine flameout prevention control method according to any one of claims 1 to 6, characterized in that: In step S3, during the self-learning process, the anti-stall control algorithm will continuously update the decision model according to the feedback signal and gradually move towards the optimal solution.

9. The aircraft engine flameout prevention control method according to claim 8, characterized in that: The feedback signal includes external environment changes and engine hardware loss parameters.

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