Engine rotor ignition device and ignition control method

Abstract

The application belongs to the technical field of engine test, and particularly relates to an engine rotor priming device and a priming control method. The device comprises: a first signal line (1) fixed on a stator component, a second signal line (2) fixed on a rotor component, the first signal line (1) and the second signal line (2) coupled through inductive power supply mode coil, the first signal line (1) connected to a resonant power amplifier module, and the second signal line (2) connected to a detonator; a single-chip microcomputer used for sending a control signal and an excitation signal according to a host computer instruction, the control signal configured to control the on-off of a direct current stabilized power supply to the resonant power amplifier module, the excitation signal serving as a power amplifier input of the resonant power amplifier module, and a current for detonating the detonator generated based on the resonant power amplifier module. The engine rotor priming device has simple structure, safe and reliable installation, small blade modification amount, and can blast when the blade rotates to a specified phase.

Description

Technical Field

[0001] This application belongs to the field of engine testing technology, specifically relating to an engine rotor detonation device and detonation control method. Background Technology

[0002] Before an aircraft engine is finalized for production, it must undergo an engine containment test. Currently, there are two methods to control rotor blade slippage during containment testing: one is to set a speed at which a pre-fabricated defect causes the blade to break, and the other is to deliberately detonate a blasting cord to break the blade once the speed is reached. The pre-fabricated defect method is no longer widely used because it cannot meet the accuracy requirements for speed control and cannot achieve phase control of rotor blade slippage.

[0003] Currently, there are two common methods for detonating rotor blades: one uses a pre-energized detonator to introduce external power into the rotor assembly for detonation control; the other uses remote detonation to achieve blade flight, utilizing wirelessly transmitted PCM encoded commands to control a detonation controller installed on the rotor. Of the two existing methods, the pre-energized method requires significant engine modifications. The impact of the pre-energized detonator bracket on the intake casing and engine structural characteristics during rotor blade flight is also difficult to assess. The remote detonation method involves installing the detonator ignition power supply and controller inside the engine rotor, posing a risk of accidental detonation due to control system failure. Neither method controls the detonation phase. If casing impact response measurement is required at the moment of detonation, sensors would need to be arranged around the circumference, and some locations would interfere with external piping, making installation impossible. This wastes sensor resources and carries the risk of not obtaining data. Summary of the Invention

[0004] To address one of the aforementioned problems, this application provides an engine rotor detonation device and detonation control method for detonating the rotor blades at a designated position.

[0005] The first aspect of this application provides an engine rotor detonation device, comprising:

[0006] The first signal line is fixed on the stator component, and the first signal line forms a first end on the stator component that couples with the second signal line, and a second end that is connected to the resonant power amplifier module outside the engine.

[0007] The second signal line is fixed on the rotor component. The second signal line forms a first end on the rotor component that couples with the first signal line, and a second end that is connected to the detonator installed at the root of the blade.

[0008] The microcontroller is used to issue control signals and excitation signals according to the instructions of the host computer. The control signals are configured to control the power supply of the DC regulated power supply to the resonant power amplifier module. The excitation signals serve as the power amplifier input of the resonant power amplifier module, and the resonant power amplifier module generates a current for detonating the detonator.

[0009] Preferably, the host computer includes:

[0010] The detonation delay calculation module is used to calculate the detonation delay. The detonation delay is determined by the actual delay and the required delay. The actual delay is the delay caused by the detonator itself detonating and the induction power supply coil reaching the detonation voltage after the microcontroller sends control and excitation signals. The required delay is the delay calculated based on the preset detonation phase and the current engine speed.

[0011] The detonation trigger signal generation module is used to acquire manual detonation signals, record detonation-related data, and perform system self-checks. When the self-check passes, it generates a detonation trigger signal.

[0012] The control parameter sending module is used to send the detonation trigger signal and detonation delay parameters to the microcontroller, which then determines the timing for issuing the control signal and excitation signal.

[0013] Preferably, the detonation delay calculation module includes a rotational speed calculation unit, which is used to locate the blade to be detonated by an external sensor and calculate the current engine speed based on the time difference between two passes of the blade to be detonated by the sensor.

[0014] A second aspect of this application provides an engine rotor detonation control method for controlling the detonation of the aforementioned engine rotor detonation device. The detonation control method includes:

[0015] Step S1: Calculate the detonation delay. The detonation delay is determined by the actual delay and the required delay. The actual delay is the delay caused by the detonator itself detonating and the induction power supply coil reaching the detonation voltage after the microcontroller sends the control signal and excitation signal. The required delay is the delay calculated based on the preset detonation phase and the current engine speed.

[0016] Step S2: Obtain the manual detonation signal, record the detonation-related data, and perform a system self-check. Once the self-check is passed, a detonation trigger signal is generated.

[0017] Step S3: Send the detonation trigger signal and detonation delay parameters to the microcontroller, which then determines the timing for issuing the control signal and excitation signal.

[0018] Preferably, in step S1, the blade to be blasted is located by an external sensor, and the current engine speed is calculated based on the time difference between the two times the blade passes the sensor.

[0019] Preferably, the microcontroller activates the data acquisition device and the high-speed camera data recording device based on the detonation delay parameters, thereby realizing the linkage control function of the recording device.

[0020] Preferably, before the engine rotor detonation control, the entire test system is further debugged by replacing the detonator with a combination of light-emitting diodes and resistors, and simulating the detonation of the detonator by lighting up the diodes during rotation.

[0021] Preferably, the system self-test in step S2 includes:

[0022] The system checks whether the operation status of each system or device of the engine rotor detonation device is normal. If it is normal, a self-test pass signal is given; otherwise, an abnormality is indicated for the corresponding system or device, and the control personnel decide whether to retest or terminate the detonation procedure.

[0023] The proposed engine rotor detonation device has a simple structure, is safe and reliable to install, requires minimal modification to the blades, and can detonate when the blades rotate to a specified phase. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the signal line installation of a preferred embodiment of the engine rotor initiation device of this application.

[0025] Figure 2 This is a system architecture diagram of a preferred embodiment of the engine rotor initiation device of this application.

[0026] Figure 3 This is a flowchart of a preferred embodiment of the engine rotor detonation control method of this application.

[0027] Figure 4 For this application Figure 3 The system self-test flowchart of the embodiment shown.

[0028] Wherein, 1 is the first signal line and 2 is the second signal line. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0030] This application first provides an engine rotor detonation device, such as Figure 1 and Figure 2 As shown, it mainly includes:

[0031] The first signal line 1 is fixed on the stator component. The first signal line 1 forms a first end on the stator component that couples with the second signal line 2, and a second end that is connected to the resonant power amplifier module outside the engine.

[0032] The second signal line 2 is fixed on the rotor component. The second signal line 2 forms a first end on the rotor component that couples with the first signal line 1, and a second end that is connected to the detonator installed at the root of the blade.

[0033] The microcontroller is used to issue control signals and excitation signals according to the instructions of the host computer. The control signals are configured to control the power supply of the DC regulated power supply to the resonant power amplifier module. The excitation signals serve as the power amplifier input of the resonant power amplifier module, and the resonant power amplifier module generates a current for detonating the detonator.

[0034] This application utilizes inductive power supply to detonate the detonator, ignite the explosive, and sever the blades. Specifically, an antenna coil structure, also known as an inductive coupling coil, is added between the rotor and stator components. This inductive coupling coil is divided into rotor and stator parts, each placed on the engine's rotor and stator respectively, to complete the transmission of detonation control power between the rotor and stator. Figure 1 The diagram shows a wrap-around coupling method, but an end-face coupling method can also be designed according to actual conditions. In the diagram, the second signal line 2 is connected to the blade root and then to the detonator. The first signal line 1 extends along the path of the stator component all the way to the outside of the engine and is connected to the resonant power amplifier module. In a specific embodiment, the first signal line 1 and the second signal line 2 are pressed onto the structural surface of the rotor stator by tape.

[0035] It is understandable that both the first signal line 1 and the second signal line 2 are loop coils. The first and second ends, as described above, are the two ends formed by the extension of the signal line on the rotor or stator, and do not refer to the ends of the lines.

[0036] In some alternative implementations, the host computer includes:

[0037] The detonation delay calculation module is used to calculate the detonation delay. The detonation delay is determined by the actual delay and the required delay. The actual delay is the delay caused by the detonator itself detonating and the induction power supply coil reaching the detonation voltage after the microcontroller sends control and excitation signals. The required delay is the delay calculated based on the preset detonation phase and the current engine speed.

[0038] The detonation trigger signal generation module is used to acquire manual detonation signals, record detonation-related data, and perform system self-checks. When the self-check passes, it generates a detonation trigger signal.

[0039] The control parameter sending module is used to send the detonation trigger signal and detonation delay parameters to the microcontroller, which then determines the timing for issuing the control signal and excitation signal.

[0040] First, it should be noted that this application can detonate the blade at a predetermined phase, that is, when the blade rotates to a set position to detonate. For this purpose, it is necessary to calculate the required delay based on the preset detonation phase and rotation speed. The time taken for the phase of the blade to be detonated at a certain moment to rotate to the preset detonation phase according to the current rotation speed is the required delay, for example, 5ms. That is, the detonator needs to be detonated after 5ms. Then, based on the physical delay characteristics of the detonator itself, such as the detonation itself, it is calculated how long the detonator needs to detonate after the detonation control signal is issued, which is the actual delay, for example, 2ms. At this time, it can be calculated that the detonation control signal needs to be issued after 3ms.

[0041] refer to Figure 2 This embodiment employs high-frequency inductive power supply and operates in AC initiation mode. For group initiation, multiple detonators are used in parallel. The system consists of a host computer, a microcontroller, a regulated power supply, a resonant power amplifier module, and coupled induction coils. The host computer measures engine speed and zero-phase point. It inputs the detonation phase calculation control, issues the detonation control signal, and records the start signal time. It also controls the microcontroller's operation. The microcontroller receives the engine's zero-phase point, the detonation control signal delay, records the start signal time, and periodically issues control and excitation signals. The DC regulated power supply provides the detonator initiation current through the resonant power amplifier module. The upper limit current is 6A, and the voltage is 8V. The maximum output of the resonant power amplifier is 48W. In this embodiment, for each type of engine, impedance matching of the induction power supply coil is required based on the number of detonators and the total resistance. A suitable induction coil is designed to improve transmission efficiency, reduce system delay time difference, and improve the control accuracy of the detonation phase.

[0042] In some optional embodiments, the detonation delay calculation module includes a rotational speed calculation unit, which is used to locate the blade to be detonated by an external sensor and calculate the current engine speed based on the time difference between two passes of the blade to be detonated by the sensor.

[0043] The external sensor in this embodiment can also perform phase tracking of the exploding blades based on rotational speed calculations.

[0044] The second aspect of this application provides a method for controlling the detonation of an engine rotor, thereby controlling the detonation of the aforementioned engine rotor detonation device, such as... Figure 3 As shown, the detonation control method includes:

[0045] Step S1: Calculate the detonation delay. The detonation delay is determined by the actual delay and the required delay. The actual delay is the delay caused by the detonator itself detonating and the induction power supply coil reaching the detonation voltage after the microcontroller sends the control signal and excitation signal. The required delay is the delay calculated based on the preset detonation phase and the current engine speed.

[0046] Step S2: Obtain the manual detonation signal, record the detonation-related data, and perform a system self-check. Once the self-check is passed, a detonation trigger signal is generated.

[0047] Step S3: Send the detonation trigger signal and detonation delay parameters to the microcontroller, which then determines the timing for issuing the control signal and excitation signal.

[0048] In this embodiment, the engine speed is first measured, and the system delay time is calculated based on the detonation phase angle and engine speed. Then, the system waits for the detonation command. Upon arrival of the detonation command, a detonation signal is issued based on the rotor synchronization signal and the delay time. A recording start signal is given according to the design specifications.

[0049] In some alternative implementations, in step S1, the blade to be blasted is located using an external sensor, and the current engine speed is calculated based on the time difference between the two times the blade passes the sensor.

[0050] In some alternative implementations, the microcontroller activates the data acquisition device and the high-speed camera data recording device based on the detonation delay parameters, thereby realizing the linkage control function of the recording device.

[0051] In some alternative implementations, prior to the engine rotor detonation control, the test system is further debugged by replacing the detonator with a combination of light-emitting diodes and resistors. During rotation, the diodes are lit to simulate the detonation of the detonator. The debugging process does not damage the engine and ensures the smooth progress of the formal test.

[0052] In some alternative implementations, such as Figure 4 As shown, the system self-test in step S2 includes:

[0053] The system checks whether the operation status of each system or device of the engine rotor detonation device is normal. If it is normal, a self-test pass signal is given; otherwise, an abnormality is indicated for the corresponding system or device, and the control personnel decide whether to retest or terminate the detonation procedure.

[0054] In this embodiment, the main purpose is to check the working status of each part of the detonation system and the system delay setting. Based on the inspection results, a description is given as to whether the test is allowed, such as choosing to end the system process, ending the entire program, instructing the test bench to pull the engine back to idle, then stopping the machine, and performing individual checks after stopping, etc.

[0055] This application allows for convenient structural modification of the engine rotor detonation device, without being limited by modification volume or rotation radius, without damaging the engine structure, and without affecting the engine's test performance.

[0056] Although this application has been described in detail above with general descriptions and specific embodiments, some modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, such modifications or improvements made without departing from the spirit of this application are all within the scope of protection claimed in this application.

Claims

1. An engine rotor ignition device, characterized by, It comprises: A first signal line (1) is fixed on the stator component, and the first signal line (1) forms a first end coupled with the second signal line (2) on the stator component and a second end connected to the resonant power amplifier module outside the engine; A second signal line (2) is fixed on the rotor component, and the second signal line (2) forms a first end coupled with the first signal line (1) on the rotor component and a second end connected to the detonator installed at the blade root; A single-chip microcomputer is used to send control signals and excitation signals according to the instructions of the upper computer, the control signals are configured to control the on-off of the power supply of the direct current stabilized power supply to the resonant power amplifier module, and the excitation signals are used as the power amplifier input of the resonant power amplifier module to generate the current for detonating the detonator based on the resonant power amplifier module.

2. The engine rotor ignition device of claim 1, wherein The upper computer comprises: A detonation delay calculation module is used to calculate the detonation delay, and the detonation delay is determined by the actual delay and the required delay, the actual delay is the delay generated after the single-chip microcomputer sends the control signals and the excitation signals, the detonator itself detonates and the induction power supply coil reaches the detonation voltage, and the required delay refers to the delay calculated according to the preset blasting phase and the current engine speed; An ignition trigger signal generation module is used to obtain a manual detonation signal, record detonation related data, and perform system self-checking, and when the self-checking is passed, an ignition trigger signal is generated; A control parameter sending module is used to send the ignition trigger signal and the detonation delay parameter to the single-chip microcomputer to determine the timing of sending the control signals and the excitation signals.

3. The engine rotor ignition device of claim 2, wherein The detonation delay calculation module comprises a speed calculation unit, which is used to position the blade to be blasted by an external sensor and calculate the current engine speed according to the time difference of the blade to be blasted passing through the sensor twice.

4. An engine rotor ignition initiation control method characterized by, The detonation control method of the engine rotor detonation device of any one of claims 1-3 comprises: Step S1, calculating the detonation delay, and the detonation delay is determined by the actual delay and the required delay, the actual delay is the delay generated after the single-chip microcomputer sends the control signals and the excitation signals, the detonator itself detonates and the induction power supply coil reaches the detonation voltage, and the required delay refers to the delay calculated according to the preset blasting phase and the current engine speed; Step S2, obtaining a manual detonation signal, recording detonation related data, and performing system self-checking, and when the self-checking is passed, an ignition trigger signal is generated; Step S3, sending the ignition trigger signal and the detonation delay parameter to the single-chip microcomputer to determine the timing of sending the control signals and the excitation signals.

5. The engine rotor ignition initiation control method of claim 4 wherein, In step S1, the blade to be blasted is positioned by an external sensor, and the current engine speed is calculated according to the time difference of the blade to be blasted passing through the sensor twice.

6. The engine rotor ignition initiation control method of claim 4 wherein, The single-chip microcomputer starts the data acquisition equipment and the high-speed camera data recording equipment according to the detonation delay parameter to realize the linkage control function of the recording equipment.

7. The engine rotor ignition initiation control method of claim 4 wherein, Before the engine rotor detonation control, further comprising replacing the detonator with a combination of light-emitting diodes and resistors, and simulating the detonation of the detonator by lighting the diodes during rotation to debug the entire test system.

8. The engine rotor ignition initiation control method of claim 4 wherein, The system self-checking in step S2 comprises: Detecting whether the working state of each system or device of the engine rotor initiation device is normal, if normal, giving a self-check passing signal, otherwise giving a prompt of abnormality of the corresponding system or device, and selecting by the control personnel whether to re-detect or end the initiation procedure.

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