Air turbine starter overspeed protection control method and system
Patent Information
- Application Number
- CN202510554333.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-29
- Publication Date
- 2026-10-30
AI Technical Summary
[0025]本申请通过对航空发动机起动阶段涡轮起动机转速数据与发动机燃气涡轮转速数据进行采集，并基于涡轮起动机转速数据与发动机燃气涡轮转速数据以及基于涡轮起动机转速数据与发动机燃气涡轮转速数据得到的二者差值数据，可自动识别空气涡轮起动机各种故障模式采取对应的故障处置对策，并向飞机申报对应故障告警信息，飞行员可根据故障提示及时采取对应处理措施，提高发动机使用安全性。
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Figure CN123006451A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aero-engine technology, specifically relating to an overspeed protection control method and system for an air turbine starter. Background Technology
[0002] Air turbine starters are generally used for starting aircraft engines. Their main purpose is to provide starting torque for the aircraft engine. When the engine starts, a high-pressure gas is drawn from the compressor of the Auxiliary Power Unit (APU) and driven through the air pipeline to rotate the air turbine starter (ATS) connected to the engine gearbox. This does work (converts air kinetic energy into mechanical energy), thereby increasing the speed of the aircraft engine and finally completing the start. After the engine starts successfully, the control system cuts off the air supply to the APU, and the air turbine starter stops working.
[0003] During engine starting, malfunctions such as a faulty solenoid valve in the air supply line failing to cut off the air supply, or a faulty overrunning clutch in the air turbine starter, can lead to excessively high air turbine starter speeds, causing problems like rotor overrun and breakage. To ensure safety during starting, engine speed signals are typically collected. When the collected engine speed exceeds the limit, the controller issues an overrunning alarm signal, which the pilot then judges and handles based on the actual flight conditions. However, this method only warns of overrunning starter speed and relies on the pilot's judgment and control, failing to identify different fault modes such as rotor jamming, low air pressure, output shaft breakage causing overrunning, failure to disconnect the air supply causing overrunning, and overrunning caused by overrunning clutch malfunction. Consequently, it cannot take targeted fault handling measures to prevent secondary damage and ensure flight safety. In certain special conditions, the pilot may not be able to promptly determine whether the air turbine starter is faulty based on limited information, thus missing the opportunity to take corrective action and causing greater damage to the starter, engine, and even the aircraft.
[0004] Application content
[0005] The purpose of this application is to provide an overspeed protection control method and system for an air turbine starter, so as to solve the problem mentioned in the background art that existing aero-engines cannot accurately obtain fault information during the start-up process.
[0006] To achieve the above objectives, this application provides the following technical solution: a method for overspeed protection control of an air turbine starter, comprising:
[0007] Collect turbine starter speed data and engine gas turbine speed data during the start-up phase of an aero-engine, which includes a process phase and a completion phase;
[0008] Based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data and / or the engine gas turbine speed data, start-up status information is output and / or control commands are executed.
[0009] Furthermore, the process phase includes an initial process phase, where starting status information is output and / or control commands are executed based on the difference between the turbine starter speed data and the engine gas turbine speed data during the starting phase, the turbine starter speed data, and / or the engine gas turbine speed data.
[0010] In the initial stage of the process, when both the turbine starter speed data and the engine gas turbine speed data are less than the first set value, the corresponding output will be a low starting air pressure or rotor jamming alarm message.
[0011] Furthermore, the first setting value is any value between 1 and 15.
[0012] Furthermore, based on the difference between the turbine starter speed data and the engine gas turbine speed data during the starting phase, the turbine starter speed data, and / or the engine gas turbine speed data, the output of starting status information and / or the execution of control commands include:
[0013] During the process phase, when the absolute value of the difference between the turbine starter speed data and the engine gas turbine speed data is not less than the second set value, the corresponding starter output shaft breakage alarm information is output and the control command to close the starter solenoid valve and cut off the starter air supply is executed.
[0014] Furthermore, the second setting value is any value between 5 and 60.
[0015] Furthermore, the process stages are engine cold run, dummy start, or start-up stages. Based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up stage, the turbine starter speed data, and / or the engine gas turbine speed data, the output of start-up status information and / or the execution of control commands include:
[0016] During the start-up process, when both the turbine starter speed data and the engine gas turbine speed data are not less than the third set value and remain at the set value for a set time, the start-up solenoid valve will not respond to the fault warning information and will execute the main control channel switching control command.
[0017] Furthermore, the third setting value is any value within the range of 50 to 60.
[0018] Furthermore, based on the difference between the turbine starter speed data and the engine gas turbine speed data during the starting phase, the turbine starter speed data, and / or the engine gas turbine speed data, the output of starting status information and / or the execution of control commands include:
[0019] During the completion phase, when the engine gas turbine speed data is not less than the fourth set value and the absolute value of the difference between the turbine starter speed data and the engine gas turbine speed data is not greater than the fifth set value, a fault alarm message indicating that the starter cannot disengage is output.
[0020] Furthermore, the fourth setting value is any value between 60 and 90.
[0021] Another aspect of this application discloses an overspeed protection control system for an air turbine starter, comprising:
[0022] The acquisition module is configured to acquire turbine starter speed data and engine gas turbine speed data during the start-up phase of an aero-engine, which includes a process phase and a completion phase.
[0023] The control module is configured to output start-up status information and / or execute control commands based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data, and / or the engine gas turbine speed data.
[0024] Compared with the prior art, the beneficial effects of this application are:
[0025] This application collects turbine starter speed data and engine gas turbine speed data during the start-up phase of an aircraft engine. Based on the turbine starter speed data and the engine gas turbine speed data, as well as the difference between the two data, it can automatically identify various fault modes of the air turbine starter, take corresponding fault handling measures, and report corresponding fault alarm information to the aircraft. The pilot can take corresponding measures in a timely manner according to the fault prompts, thereby improving the safety of engine operation. Attached Figure Description
[0026] Figure 1 This is a schematic diagram of the method flow of this application;
[0027] Figure 2 This is a schematic diagram of an aircraft engine starting system. Detailed Implementation
[0028] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0029] An overspeed protection control method for an air turbine starter is disclosed. This protection method is used to ensure the safe starting of an aero-engine and is implemented based on the control system of the aero-engine starting system. Specifically, refer to... Figure 2 The main body of the aero-engine starting system consists of an APU (Auxiliary Power Unit), an ATS (Air Turbine Starter), and the engine. The APU and the ATS are connected via air lines, and the air lines are equipped with solenoid valves (i.e., air supply on / off solenoid valves) to control the flow of air through the lines. The starting system also includes a control system with an ECU (Electronic Control Unit). The controller in the control system can control the aero-engine starting process to ensure the safety of the aero-engine starting. For example, the controller can control the operation of the air supply on / off solenoid valve based on the turbine starter speed data and the engine gas turbine speed data. The control system can also output engine status information (such as fault alarm information) according to the starting status. Correspondingly, the starting system can also include a display interface connected to the control system to display engine status information such as fault alarm information that occurs during the starting process in real time, so as to remind relevant personnel to pay attention and take action.
[0030] Specifically, refer to Figure 1 The above protection methods include:
[0031] S100: Collect turbine starter speed data and engine gas turbine speed data during the start-up phase of the aero-engine, the start-up phase including the process phase and the completion phase;
[0032] S200: Outputs start-up status information and / or executes control commands based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data, and / or the engine gas turbine speed data.
[0033] In some embodiments, the turbine starter speed data and the engine gas turbine speed data are both ratio data. Specifically, the turbine starter speed data is the ratio of the turbine starter speed to the turbine starter rated speed, and the engine gas turbine speed data is the ratio of the engine gas turbine speed to the engine gas turbine rated speed.
[0034] In some embodiments, the above process stages are engine cold run, dummy start, or start-up process stages.
[0035] In some embodiments, the process phase includes an initial process phase, which represents a time period of a seconds after receiving a start command from the control system (e.g., a start command from the controller). Specifically, for example, the start command from the control system is recorded as the timing start point, and the initial process phase represents a time period of 0 to a seconds. In some examples, a is any value from 5 to 20.
[0036] In some embodiments, the aforementioned completion stage is the engine start-up success stage, which is the time period after the engine starts successfully.
[0037] In some embodiments, the aforementioned start-up status information may include various alarm information. Correspondingly, the pilot may perform operations such as stopping the aircraft based on various alarm information to ensure the safety of starting. For example, alarm information may include, for example, low start-up air pressure, rotor jamming, or starter output shaft breakage.
[0038] In some embodiments, outputting start-up status information and / or executing control commands based on the difference between turbine starter speed data and engine gas turbine speed data during the start-up phase, turbine starter speed data, and / or engine gas turbine speed data includes:
[0039] In the initial stage of the process, when both the turbine starter speed data and the engine gas turbine speed data are less than the first set value, the corresponding output will be a low starting air pressure or rotor jamming alarm message.
[0040] For example, the first setting value mentioned above is any value between 1 and 15.
[0041] In some embodiments, outputting start-up status information and / or executing control commands based on the difference between turbine starter speed data and engine gas turbine speed data during the start-up phase, turbine starter speed data, and / or engine gas turbine speed data includes:
[0042] During the process phase, when the absolute value of the difference between the turbine starter speed data and the engine gas turbine speed data is not less than the second set value, the corresponding starter output shaft breakage alarm information is output and the starter solenoid valve is closed and the starter air supply control command is executed.
[0043] In some examples, the second set value is any value between 5 and 60, and the control command is executed by the control system controlling the solenoid valve, that is, by controlling the solenoid valve to close and cut off the starter air supply through the controller.
[0044] In some embodiments, outputting start-up status information and / or executing control commands based on the difference between turbine starter speed data and engine gas turbine speed data during the start-up phase, turbine starter speed data, and / or engine gas turbine speed data includes:
[0045] During the start-up process, when both the turbine starter speed data and the engine gas turbine speed data are not less than the third set value and remain at the set value for a set time, the start-up solenoid valve will not respond to the fault warning information and will execute the main control channel switching control command.
[0046] In this example, when the pilot receives a fault warning message that the starter solenoid valve is not responding, the pilot should shut down the APU as soon as possible to prevent the starter motor from over-revving and breaking.
[0047] In some embodiments, the third setting value is any value between 50 and 60, and the setting time is, for example, 3 seconds. Specifically, when both the turbine starter speed data and the engine gas turbine speed data are not less than the third setting value and remain at the set time, it means that at any point in the starting process, the collected turbine starter speed data and engine gas turbine speed data are not less than the third setting value and do not decrease within the set time. That is, if the maintenance time of both the turbine starter speed data and the engine gas turbine speed data being not less than the third setting value exceeds the set time, it is determined that the solenoid valve is not responding.
[0048] In some embodiments, outputting start-up status information and / or executing control commands based on the difference between turbine starter speed data and engine gas turbine speed data during the start-up phase, turbine starter speed data, and / or engine gas turbine speed data includes:
[0049] During the completion phase, when the engine gas turbine speed data is not less than the fourth set value and the absolute value of the difference between the turbine starter speed and the engine gas turbine speed is not greater than the fifth set value, a fault alarm message indicating that the starter cannot disengage is output.
[0050] Correspondingly, when the pilot receives a fault alarm message indicating that the starter motor cannot disengage, he can shut down the engine based on the actual situation to prevent the starter motor from over-rotating and breaking.
[0051] In some embodiments, the fourth setting value is any value between 60 and 90, and the fifth setting value is, for example, 1.
[0052] Another aspect of this application discloses an overspeed protection control system for an air turbine starter, the system comprising:
[0053] The data acquisition module is configured to acquire turbine starter speed data and engine gas turbine speed data during the start-up phase of an aero-engine, which includes a process phase and a completion phase.
[0054] The control module is configured to output start-up status information and / or execute control commands based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data, and / or the engine gas turbine speed data.
[0055] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.
[0056] In the description of this application, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this application, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine different embodiments or examples and features of different embodiments or examples described in this application.
[0057] Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.
Claims
1. A method for overspeed protection control of an air turbine starter, characterized in that, include: Collect turbine starter speed data and engine gas turbine speed data during the start-up phase of an aero-engine, which includes a process phase and a completion phase; Based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data and / or the engine gas turbine speed data, start-up status information is output and / or control commands are executed.
2. The overspeed protection control method for an air turbine starter according to claim 1, characterized in that: The process phase includes an initial phase, which outputs start-up status information and / or executes control commands based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data, and / or the engine gas turbine speed data. In the initial stage of the process, when both the turbine starter speed data and the engine gas turbine speed data are less than the first set value, the corresponding output will be a low starting air pressure or rotor jamming alarm message.
3. The overspeed protection control method for an air turbine starter according to claim 2, characterized in that: The first setting value is any value between 1 and 15.
4. The overspeed protection control method for an air turbine starter according to claim 1, characterized in that: Based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data and / or the engine gas turbine speed data, starter status information is output and / or control commands are executed, including: During the process phase, when the absolute value of the difference between the turbine starter speed data and the engine gas turbine speed data is not less than the second set value, the corresponding starter output shaft breakage alarm information is output and the control command to close the starter solenoid valve and cut off the starter air supply is executed.
5. The overspeed protection control method for an air turbine starter according to claim 4, characterized in that: The second setting value is any value between 5 and 60.
6. The overspeed protection control method for an air turbine starter according to claim 1, characterized in that: The process phase includes engine cold run, dummy start-up, or start-up phases. Based on the difference between turbine starter speed data and engine gas turbine speed data during the start-up phase, turbine starter speed data, and / or engine gas turbine speed data, the output of start-up status information and / or the execution of control commands include: During the start-up process, when both the turbine starter speed data and the engine gas turbine speed data are not less than the third set value and remain at the set value for a set time, the start-up solenoid valve will not respond to the fault warning information and will execute the main control channel switching control command.
7. The overspeed protection control method for an air turbine starter according to claim 6, characterized in that: The third setting value is any value between 50 and 60.
8. The overspeed protection control method for an air turbine starter according to claim 1, characterized in that: Based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data and / or the engine gas turbine speed data, starter status information is output and / or control commands are executed, including: During the completion phase, when the engine gas turbine speed data is not less than the fourth set value and the absolute value of the difference between the turbine starter speed data and the engine gas turbine speed data is not greater than the fifth set value, a fault alarm message indicating that the starter cannot disengage is output.
9. The overspeed protection control method for an air turbine starter according to claim 8, characterized in that: The fourth setting value is any value between 60 and 90.
10. An overspeed protection control system for an air turbine starter, characterized in that, include: The acquisition module is configured to acquire turbine starter speed data and engine gas turbine speed data during the start-up phase of an aero-engine, which includes a process phase and a completion phase. The control module is configured to output start-up status information and / or execute control commands based on the difference between the turbine starter speed data and the engine gas turbine speed data during the start-up phase, the turbine starter speed data, and / or the engine gas turbine speed data.