Adjusting system and method for main hydraulic actuator cylinder and auxiliary hydraulic actuator cylinder of aero-engine

Abstract

The invention discloses an adjustment system and method for main and auxiliary hydraulic actuator cylinders of an aero-engine, and the system comprises a compressor guide vane angle adjustment control model which is used for building a control relation between guide vane angle control parameters and engine parameters, and recognizing the adjustment angle difference of the main and auxiliary guide vane actuator cylinders; the logic control module is used for defining a control program of a digital electronic controller according to the angle difference of the main guide vane actuator cylinder and the auxiliary guide vane actuator cylinder; wherein the control program of the digital electronic controller comprises a control signal; the mechanical limit adjusting module is used for responding to the control signal and realizing mechanical regulation and control of the actuating cylinder driving rod; the parameter extraction module is used for evaluating whether design requirements are met or not and outputting an evaluation result; and the adjusting module is used for acquiring the evaluation result and controlling the logic control module to realize logic control. According to the technical scheme, it can be effectively guaranteed that the actual working characteristics of the engine are executed according to the guide vane control plan; and the hysteresis influence caused by a mechanism gap formed by manufacturing and mounting is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and in particular to an adjustment system for primary and secondary hydraulic cylinders of aircraft engines. Background Art

[0002] With the development of aircraft engine technology, the requirements for performance and safety are constantly increasing. In order to meet the needs of safe operation of aircraft engines under high speed, high temperature, variable load and other conditions, higher requirements are placed on the fault tolerance of the engine hydraulic actuator.

[0003] Due to the limitations of working environment and manufacturing factors, the existing guide vane adjustment mechanism of aircraft engines has the following defects: due to the high aerodynamic sensitivity of the compressor and the inevitable gaps in the manufacture and installation of the guide vane adjustment mechanism, the friction difference of the actuator, the rigidity of the actuator ring, the damping and other factors, the angle synchronization of the main and auxiliary hydraulic actuators of the compressor guide vane adjustment mechanism is not good during the operation of the engine, and the maximum angle difference of the displacement sensor of the main and auxiliary actuators is 2° to 3°. Therefore, it interferes with the judgment and execution of the control system and the control plan, and has a great impact on the flow characteristics of the compressor, resulting in unstable engine performance and large differences in the same engine during multiple runs and different test runs. It can be seen that when the aircraft engine is in working condition, due to the poor adjustment tolerance of the main and auxiliary hydraulic actuators, the inlet adjustable guide vanes (IGV) of the compressor fail to reach the specified angle according to the control requirements, which will cause the performance parameters of the aircraft engine to fluctuate and deviate, and interfere with the control plan, causing the engine thrust, stability, etc. to fail to meet the normal working characteristics of the engine, and in severe cases, it will cause engine surge or stall problems. Summary of the invention

[0004] In order to solve the above problems, the present application provides an adjustment system for the main and auxiliary hydraulic actuators of an aircraft engine, comprising:

[0005] Compressor guide vane angle adjustment control model: used to establish the control relationship between the guide vane angle control parameters and the engine parameters; based on the control relationship, identify the adjustment angle difference between the main and auxiliary guide vane actuators;

[0006] Logic control module: used to define the control program of the digital electronic controller according to the adjustment angle difference of the main and auxiliary guide vane actuators, and realize the logic control between the main and auxiliary compressor guide vane actuators and the centrifugal booster pump, the main fuel plunger pump, and the low-pressure fuel filter; wherein the control program of the digital electronic controller includes control signals;

[0007] Mechanical limit adjustment module: used to respond to control signals and realize mechanical regulation of the actuator drive rod;

[0008] Parameter extraction module: used to record the performance parameters of the whole engine under different working conditions, compare them with the overall matching design results, evaluate whether they meet the design requirements, and output the evaluation results;

[0009] Adjustment module: used to obtain the evaluation result and control the logic control module to implement logic control.

[0010] Among them, the guide vane angle control parameters include: compressor guide vane angle Afa2, high-pressure rotor converted speed N2r, low-pressure rotor converted speed N1r, and throttle lever angle PLA.

[0011] Engine parameters include: thrust F, fuel consumption rate sfc, compressor pressure ratio π, flow rate Q, efficiency η and engine operating status.

[0012] Furthermore, the mechanical limit adjustment module controls the main guide vane actuator cylinder drive rod and the auxiliary guide vane actuator cylinder drive rod according to the control signal, and jointly drives the compressor adjustable guide vane actuator ring to achieve adjustment of the compressor inlet guide vane row.

[0013] Wherein, when controlling the driving rod of the main guide vane actuator cylinder and the driving rod of the auxiliary guide vane actuator cylinder, the mechanical limit working ranges of the driving rod of the main guide vane actuator cylinder and the driving rod of the auxiliary guide vane actuator cylinder are respectively limited.

[0014] Furthermore, the control signal includes a start condition and a control instruction; the control instruction includes: a start opening speed and an end opening speed; the start condition is a parameter threshold value of a guide vane angle control parameter and an engine parameter.

[0015] The control program of the digital electronic controller includes: an acceleration guide vane control program and a deceleration readjustment guide vane control program.

[0016] On the other hand, the present invention provides a method for adjusting the main and auxiliary hydraulic actuators of an aircraft engine, comprising the following steps:

[0017] Establish the control relationship between the guide vane angle control parameters and the engine parameters; based on the control relationship, identify the adjustment angle difference between the main and auxiliary guide vane actuators;

[0018] According to the adjustment angle difference of the main and auxiliary guide vane actuators, a control program of a digital electronic controller is defined to realize the logic control between the main and auxiliary compressor guide vane actuators and the centrifugal booster pump, the main fuel plunger pump, and the low-pressure fuel filter; wherein the control program of the digital electronic controller includes a control signal;

[0019] According to the control signal, the mechanical regulation of the actuator drive rod is realized;

[0020] Record the engine performance parameters under different working conditions, compare them with the overall matching design results, evaluate whether they meet the design requirements, and output the evaluation results;

[0021] Acquire the evaluation result, and control the logic control module to implement logic control.

[0022] The adjustment system and method provided by the present invention can increase the robustness of the compressor guide vane control program in terms of compressor performance, ensure the consistency of the compressor guide vane angle during engine operation, and improve the uniformity of the compressor flow field; effectively ensure that the actual working characteristics of the engine are executed according to the guide vane control plan; reduce the hysteresis effect caused by the mechanism gap formed during manufacturing and installation; and improve the operational convenience of the engine performance adjustment needs during the test run. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic structural diagram of an adjustment system of a main and auxiliary hydraulic actuator of an aircraft engine provided according to an embodiment of the present invention;

[0024] Figure 2 It is a flow chart of a method for adjusting the main and auxiliary hydraulic actuators of an aircraft engine provided according to an embodiment of the present invention;

[0025] Figure 3 is a schematic diagram of a control program of a regulation system provided according to an embodiment of the present invention;

[0026] Figure 4 is a schematic diagram of a control process of a regulation system provided according to an embodiment of the present invention;

[0027] Figure 5 It is a structural schematic diagram of a mechanical limit adjustment module in an adjustment system provided according to an embodiment of the present invention. DETAILED DESCRIPTION

[0028] The present invention proposes a regulation system and method for main and auxiliary hydraulic actuators of aircraft engines, constructs a compressor guide vane angle regulation law based on the overall matching design result of the aircraft engine, clarifies the control relationship between the main and auxiliary compressor guide vane actuators and the centrifugal boost pump, the main fuel plunger pump and the low-pressure fuel filter by optimizing and adjusting the control program of the digital electronic controller, so as to realize the control of the main and auxiliary compressor guide vane actuators according to the established plan; at the same time, the hydraulic actuator drive rod is limited, so that the main and auxiliary guide vane actuators jointly drive the adjustment of the compressor inlet guide vane row, so as to achieve a consistent adjustment effect.

[0029] The specific implementation of the present invention is described in detail below with reference to the accompanying drawings.

[0030] Figure 1 A structural schematic diagram of the adjustment system of the main and auxiliary hydraulic actuators of an aircraft engine is provided, including the following contents:

[0031] S100 compressor guide vane angle adjustment control model:

[0032] The present invention first carries out the overall matching design of the engine, comprehensively considers the aerodynamic stability, transition state, transient performance changes and robustness, and establishes a logical model of the compressor inlet guide vane (IGV) control program and engine performance parameters (speed, pressure ratio, temperature, thrust, etc.), namely: the compressor guide vane angle adjustment control model.

[0033] Through the compressor guide vane angle adjustment control model, the control relationship between the guide vane angle control parameters and the engine parameters can be established; and the adjustment angle difference between the main and auxiliary guide vane actuators can be identified based on the control relationship. Based on this, other modules are supported to generate guide vane angle adjustment control instructions.

[0034] Specifically, the guide vane angle control parameters include: compressor guide vane angle A fa2 , High-pressure rotor conversion speed N 2r , low pressure rotor conversion speed N 1r , throttle lever angle PLA;

[0035] Engine parameters include: thrust F, fuel consumption rate sfc, compressor pressure ratio π, flow rate Q, efficiency η and engine operating status.

[0036] Through the compressor guide vane angle adjustment control model, comprehensive data analysis and problem location can be carried out based on the known defects of guide vane adjustment control, and the response characteristics between the guide vane angle control and the engine operating state can be obtained.

[0037] According to the control relationship established by the compressor guide vane angle adjustment control model, the angle difference data of the main and auxiliary hydraulic actuators can be obtained, as shown in the following table:

[0038]

[0039] It can be seen that the fans and compressors of the prior art engines generally have differences in the angles of the main and auxiliary cylinders when they are fully closed or fully opened. The difference values ​​of the adjustable guide vanes of different compressors are relatively scattered. The statistical difference of No. A01 is relatively large when it is fully opened (1.161°), and the difference is only 0.299° when it is fully closed; the difference of No. A02 is just the opposite (only 0.963° when fully opened, 1.084° when fully closed); No. A03 has relatively large differences when it is fully opened and fully closed.

[0040] S110 Logic Control Module:

[0041] The logic control module is used to define the digital electronic controller control program according to the adjustment angle difference of the main and auxiliary guide vane actuators, so as to realize the logic control between the main and auxiliary compressor guide vane actuators and the centrifugal boost pump, the main fuel plunger pump, and the low-pressure fuel filter.

[0042] The digital electronic controller control program defined in the logic control module is composed of control signals, and the control signals include starting conditions and control instructions; the control instructions include: starting opening speed and ending opening speed; the starting conditions are parameter thresholds of guide vane angle control parameters and engine parameters.

[0043] The types of digital electronic controller control programs include: acceleration guide vane control program and deceleration readjustment guide vane control program.

[0044] like Figure 3 As shown in FIG. 1 , the start conditions of the control signal of the acceleration guide vane control program are: the speed threshold is 72 and the angle threshold is -30. When these conditions are met, the start-up starts to open the speed command.

[0045] S120 mechanical limit adjustment module: used to respond to control signals and realize mechanical regulation of the actuator drive rod;

[0046] The input data of the mechanical limit adjustment module is the compressor guide vane actuator control program output by the logic control module.

[0047] like Figure 5 As shown, the mechanical limit adjustment module drives the main and auxiliary guide vane actuators according to the control parameters in the control signal, controls the main guide vane actuator drive rod and the auxiliary guide vane actuator drive rod according to the input control signal, and jointly drives the compressor adjustable guide vane actuator ring to achieve adjustment of the compressor inlet guide vane row.

[0048] When the main guide vane actuator cylinder driving rod and the auxiliary guide vane actuator cylinder driving rod are controlled, the mechanical limit working ranges of the main guide vane actuator cylinder driving rod and the auxiliary guide vane actuator cylinder driving rod are limited respectively.

[0049] In practical applications, the function of the main and auxiliary guide vane actuator drive rods E1 and E2 is to reciprocate through the force of the lubricating oil in the inner wall of the actuator to drive the compressor adjustable guide vane actuator ring, thereby driving the compressor inlet guide vane row to achieve continuous adjustment of the inlet blades. When the compressor inlet guide vane angle needs to be adjusted to the maximum, and when the parameter reading, parameter feedback, and control judgment of the angle value are consistent, the drive rod E1 of the main actuator driven by the internal lubricating oil pressure difference needs to be at the right boundary of the A1-A2 cavity (that is, the E1 drive rod works in the rightmost position). Similarly, due to the internal lubricating oil pressure difference, E2 needs to work in the right position of B1-B2. At this time, the joint force corresponding to E1 and E2 at the maximum adjustment angle is matched and consistent; similarly, due to engine reasons, when the compressor guide vane does not need to open a large angle, but closes the guide vane angle, E1 and E2 need to make their respective positions at the left boundaries of the A1-A2 cavity and the B1-B2 cavity.

[0050] Therefore, the present invention proposes that the mechanical limit working range of the main and auxiliary guide vane actuator drive rods E1 and E2 is between A1 and A2, B1 and B2 (such as Figure 5 As shown in the figure), the mechanical control target value of the actuator drive rod is realized, and the known angle deviation of the adjustment result is avoided. Through this device, the demand for engine test performance adjustment can be met, the engine test maintainability can be improved, and the actuator adjustment operation time can be shortened.

[0051] S130 parameter extraction module: used to record the performance parameters of the whole engine under different working conditions, compare them with the overall matching design results, evaluate whether they meet the design requirements, and output the evaluation results.

[0052] S140 adjustment module: used to obtain evaluation results and control the logic control module to implement logic control.

[0053] If the evaluation result does not meet the design requirements, it is necessary to trigger the logic control module to regenerate the digital electronic controller control program.

[0054] The present invention also provides a method for adjusting the main and auxiliary hydraulic cylinders of an aircraft engine through an adjustment system of the main and auxiliary hydraulic cylinders of an aircraft engine. The specific steps of the adjustment method are as follows: Figure 2 As shown:

[0055] Taking into account aerodynamic stability, transition state, transient performance changes and robustness, the adjustment law of the compressor guide vane angle is constructed based on the overall matching design results. Based on the adjustment law and the known working defects of the compressor guide vane actuator, data analysis and technical positioning are carried out; specifically, the control relationship between the guide vane angle control parameters and the engine parameters is established; according to the control relationship, the difference in the adjustment angle of the main and auxiliary guide vane actuators is identified;

[0056] According to data analysis and positioning, the guide vane actuator control program is determined: in the process, according to the adjustment angle difference of the main and auxiliary guide vane actuators, the digital electronic controller control program is defined to realize the logic control between the main and auxiliary compressor guide vane actuators and the centrifugal booster pump, the main fuel plunger pump, and the low-pressure fuel filter; wherein the digital electronic controller control program includes control signals;

[0057] Realize the mechanical limit adjustment of the main and auxiliary guide vane actuators: In this step, mechanical regulation of the actuator drive rod is realized according to the control signal;

[0058] In the iterative control and adjustment process, the engine performance parameters under different working conditions are recorded and compared with the overall matching design results to evaluate whether the design requirements are met and output the evaluation results;

[0059] The evaluation result is obtained, and the logic control module is controlled to implement logic control, thereby achieving performance parameter calibration under different working conditions.

[0060] Through the adjustment system and method of the main and auxiliary hydraulic actuators of an aircraft engine provided by the present invention, it is possible to control the working state of the engine and establish a more direct connection between the overall performance of the engine and the control parameters, thereby achieving more accurate control of the engine thrust. When applied to engines equipped with main and auxiliary actuators, it is possible to better ensure the consistency of adjustment, reduce the operating burden of the pilot, reduce fuel consumption, and reduce the possibility of danger.

[0061] The above disclosures are only several specific embodiments of the present invention; however, the present invention is not limited thereto, and any changes that can be conceived by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. An adjustment system for the main and auxiliary hydraulic cylinders of an aircraft engine, characterized in that: include: Compressor guide vane angle adjustment control model: used to establish the control relationship between guide vane angle control parameters and engine parameters; According to the control relationship, identifying the adjustment angle difference of the main and auxiliary guide vane actuators; Logic control module: used to define the digital electronic controller control program according to the adjustment angle difference of the main and auxiliary guide vane actuators, and realize the logic control between the main and auxiliary compressor guide vane actuators and the centrifugal booster pump, the main fuel plunger pump, and the low-pressure fuel filter; wherein the digital electronic controller control program includes a control signal; Mechanical limit adjustment module: used to respond to control signals and realize mechanical regulation of the actuator drive rod; Parameter extraction module: used to record the performance parameters of the whole engine under different working conditions, compare them with the overall matching design results, evaluate whether they meet the design requirements, and output the evaluation results; Adjustment module: used to obtain the evaluation result and control the logic control module to implement logic control.

2. The adjustment system according to claim 1, characterized in that: The guide vane angle control parameters include: compressor guide vane angle A fa2 , High-pressure rotor conversion speed N 2r , low pressure rotor conversion speed N 1r , throttle lever angle PLA.

3. The adjustment system according to claim 1, characterized in that: The engine parameters include: thrust F, fuel consumption rate sfc, compressor pressure ratio π, flow rate Q, efficiency η and engine working status.

4. The adjustment system according to claim 1, characterized in that: The mechanical limit adjustment module controls the main guide vane actuator cylinder drive rod and the auxiliary guide vane actuator cylinder drive rod according to the control signal, and jointly drives the compressor adjustable guide vane actuator ring to adjust the compressor inlet guide vane row.

5. The regulating system according to claim 4, characterized in that When the main guide vane actuator cylinder driving rod and the auxiliary guide vane actuator cylinder driving rod are controlled, the mechanical limit working ranges of the main guide vane actuator cylinder driving rod and the auxiliary guide vane actuator cylinder driving rod are limited respectively.

6. The adjustment system according to claim 1, characterized in that: The control signal includes a start condition and a control instruction; The control instructions include: start opening speed, end opening speed; The start-up condition is a parameter threshold value of a guide vane angle control parameter and an engine parameter.

7. The adjustment system according to claim 1, characterized in that: The control program of the digital electronic controller includes: an acceleration guide vane control program and a deceleration readjustment guide vane control program.

8. A method for adjusting the main and auxiliary hydraulic cylinders of an aircraft engine, characterized in that: The following steps are involved: Establishing a control relationship between a guide vane angle control parameter and an engine parameter; and identifying a difference in adjustment angles of a primary guide vane actuator and a secondary guide vane actuator according to the control relationship; According to the adjustment angle difference of the main and auxiliary guide vane actuators, a digital electronic controller control program is defined to realize the logic control between the main and auxiliary compressor guide vane actuators and the centrifugal booster pump, the main fuel plunger pump, and the low-pressure fuel filter; wherein the digital electronic controller control program includes a control signal; According to the control signal, the mechanical regulation of the actuator drive rod is realized; Record the engine performance parameters under different working conditions, compare them with the overall matching design results, evaluate whether they meet the design requirements, and output the evaluation results; The evaluation result is obtained, and the logic control module is controlled to implement logic control.

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