Device and method for measuring resistance of aero-engine motion mechanism under belt load condition

Abstract

The application belongs to the technical field of aero-engines, and particularly relates to a device and method for measuring the resistance force of a motion mechanism of an aero-engine under a load condition, a method and process for measuring the resistance force of the motion mechanism of the aero-engine under the load condition are provided, a device for measuring the resistance force under the load condition is designed, the resistance force of the motion mechanism of the aero-engine is more truly mastered, the design input of rigid-flex coupling dynamics analysis of the motion mechanism is provided, the adjustment precision of the motion mechanism is more accurately obtained, and the structure improvement design is guided, and the safety and reliability of the aero-engine are improved.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a device and method for measuring the drag force of aero-engine motion mechanism under load. Background Technology

[0002] As a crucial component of modern aero-engines, the motion mechanism serves two main functions: first, it alters the engine's thermodynamic cycle characteristics by changing the shape and size of the airflow channels to meet the demands of different operating conditions, ensuring good performance and stability under various circumstances; second, it improves the aircraft's maneuverability by changing the exhaust direction, shortening takeoff and landing distances, and even enabling short takeoff / vertical landing (STOVL) capabilities. The motion mechanism plays a vital role in improving engine performance, fuel economy, and aircraft maneuverability, and is widely used in modern engine design. Key components include: guide vane adjustment mechanisms and nozzle adjustment mechanisms (see [link to relevant section]). Figure 2 Including intake and exhaust actuators and other regulating mechanisms.

[0003] Due to design space and structural weight constraints, aero-engines typically have relatively thin and lightweight motion mechanisms. Under the combined effects of high-flow-rate, high-pressure aerodynamic loads (hundreds of kilograms per second) and high-temperature environmental loads, these mechanisms are highly susceptible to deformation. This deformation leads to decreased adjustment precision, changes in the flow field, and abnormal airflow excitation forces, causing high-cycle fatigue fracture of the rotor blades. Therefore, it is crucial to understand the adjustment precision of the motion mechanism. However, the complex operating conditions of an engine make it impossible to test the adjustment precision under full-engine operation. The current approach involves conducting stiffness tests on individual components, calculating the adjustment error caused by component deformation based on the test results, and summing the adjustment errors caused by each component to obtain the adjustment precision of the motion mechanism.

[0004] Its main drawbacks are: the drag force of the aero-engine motion mechanism consists of two parts: aerodynamic load and friction. During operation, the aerodynamic load increases the normal pressure on the moving pair, which increases the friction. Existing technical solutions measure the drag force under no-load conditions, which can only reflect the assembly drag force caused by factors such as assembly interference. Using this measurement result as the design input for the motion mechanism and actuator may result in problems such as excessive deformation of the motion mechanism under load or an undersized design range of the actuator driving force. During operation, the motion trajectory of the motion mechanism deviates from the ideal state, causing abnormal flow field, leading to high-cycle fatigue fracture of the blades, which affects the safety and reliability of the aero-engine. Summary of the Invention

[0005] To address the aforementioned problems, this application provides a device for measuring the drag force of aero-engine motion mechanism under load, used for testing motion mechanism test pieces. The motion mechanism test piece has multiple circumferentially distributed actuators and a linkage mechanism driven by the actuators. The linkage mechanism has an execution mechanism that needs to overcome the load. The measuring device includes:

[0006] Base plate;

[0007] The support cylinder, mounted on the base plate, is used to fix and support the test piece of the motion mechanism;

[0008] The lower support plate is fixed to the base plate, and multiple circumferentially distributed actuator cylinder seats are fixed on the lower support plate;

[0009] A loading actuator assembly is provided, with its fixed end hinged to the actuator base and its actuating end hinged to the actuator of the motion mechanism test piece, for applying a test load to the actuator.

[0010] The loading simulation device includes: a support frame, a simulated cylinder rod, an actuator cylinder, a force gauge adapter, and a force gauge;

[0011] The bracket includes an upper end face, a lower end face, and a side wall connecting the upper end face and the lower end face. The lower end face is fixed to the mounting edge of the motion mechanism test piece. The lower end face has a through hole. One end of the simulated cylinder rod passes through the through hole and is connected to the linkage mechanism, and the other end is connected to the force gauge. The actuating cylinder is installed on the outside of the upper end face. The actuating shaft of the actuating cylinder passes through the upper end face and is connected to the force gauge through the force gauge adapter.

[0012] Preferably, the actuating end of the loading actuator assembly has two ears, which are hinged to a single ear via pins and a pull rod ball, and the single ear is fixed to the actuator.

[0013] Preferably, the loading actuator cylinder assembly has a loading force gauge, which enables the loading actuator cylinder assembly to form a closed-loop control.

[0014] Preferably, the motion mechanism test piece includes a guide vane adjustment mechanism, a nozzle adjustment mechanism, and a valve adjustment mechanism.

[0015] Preferably, a method for measuring the drag force of an aero-engine motion mechanism under load conditions, comprising conducting tests using the aforementioned aero-engine motion mechanism drag force measuring device under load conditions, including:

[0016] A finite element model of the motion mechanism test piece was established using ANSYS to perform load equivalent analysis and obtain the equivalent concentrated force load under a single working condition. Load equivalent analysis was performed on different angles or displacements corresponding to multiple working conditions within the entire motion range. The equivalent concentrated force loads under different working conditions were fitted to form a time-varying load spectrum.

[0017] By controlling the loading actuator assembly to apply load to the actuator according to the time-varying load spectrum, the actuator simulates the working mode of a real engine, and the measured value of the force gauge is taken as the time-varying resistance force.

[0018] The advantages of this application include: proposing a method and process for measuring the drag force of the aero-engine motion mechanism under load conditions, designing a drag force measuring device under load conditions, more realistically understanding the drag force of the aero-engine motion mechanism, using it as design input for the rigid-flexible coupling dynamic analysis of the motion mechanism, more accurately obtaining the adjustment accuracy of the motion mechanism and guiding structural improvement design, thereby improving the safety and reliability of the aero-engine. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a preferred embodiment of the aero-engine motion mechanism adjustment accuracy measuring device of this application;

[0020] Figure 2 This is a schematic diagram of the motion mechanism test piece of this application, which is a nozzle adjustment mechanism.

[0021] Figure 3 This is a flowchart of the complete process for measuring the resistance force of the motion mechanism of an aero-engine under load, according to a preferred embodiment of this application. Detailed Implementation

[0022] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0023] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0024] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0025] The technical solution of the present invention is as follows Figure 3 As shown, a method and device for measuring the drag force of an aero-engine motion mechanism under load includes the following steps: determination of aerodynamic load simulation scheme (a), determination of time-varying load spectrum (b), determination of drag force test scheme (c), design of drag force measurement device (d), and test and result analysis (e).

[0026] The specific steps described above are explained below:

[0027] a) Step a: Analyze the structural characteristics, load type and action form of the motion mechanism, and determine the aerodynamic load simulation scheme, including load loading method and loading position. Usually, the moving cylinder is used to simulate the loading of concentrated force. This method is easy to implement and has high loading accuracy.

[0028] b) In step b, the end parts of the aero-engine motion mechanism mainly bear aerodynamic pressure, while the simulated loading of the moving cylinder can only apply concentrated force. Therefore, ANSYS is used to establish a finite element model for load equivalent analysis to obtain the equivalent concentrated force load under a single working condition. Multiple working conditions (different angles or displacements) are selected in the entire motion range for load equivalent analysis, and the equivalent concentrated force loads under different working conditions are fitted to form a time-varying load spectrum.

[0029] c) Step c, determine the resistance force measurement scheme. The resistance force can be calculated by back-calculating the pressure difference between the rod-side and rodless sides of the moving cylinder, or the resistance force can be directly measured by a force gauge. The method of directly measuring the resistance force by a force gauge is more accurate.

[0030] d) Step d: To achieve the measurement of the resistance force of the motion mechanism of an aero-engine under load conditions, a motion mechanism resistance force measuring device has been invented. The device is characterized by comprising: a single lug 1, a double lug 2, a pull rod ball 3, a pin 4, an upper support plate 5, a lower support plate 6, a base plate 7, an actuator cylinder seat 8, a simulated cylinder rod 9, a bracket 10, an actuator cylinder 11, a bolt 12, a force gauge adapter 13, a force gauge 14, a support cylinder 15, a loaded actuator cylinder assembly 16, a loaded force gauge 17, and a motion mechanism test piece 18. (See attached diagram) Figure 1 .

[0031] Specifically, it is a device for measuring the drag force of aero-engine motion mechanism under load, used to test a motion mechanism test piece 18. The motion mechanism test piece 18 has multiple circumferentially distributed actuators and a linkage mechanism driven by the actuators. The linkage mechanism has an execution mechanism that needs to overcome the load. The measuring device includes: a base plate 7; a support cylinder 15, mounted on the base plate 7, for fixing and supporting the motion mechanism test piece 18; a lower support plate 6, fixed on the base plate 7, on which multiple circumferentially distributed actuator seat 8 are fixed; and a loading actuator assembly 16, the fixed end of which is hinged to the actuator seat 8 for actuation. The actuator assembly 16 is hinged to the actuator of the motion mechanism test piece 18 and is used to apply a test load to the actuator. The loading simulation device includes: a bracket 10, a simulated cylinder rod 9, an actuating cylinder 11, a force gauge adapter 13, and a force gauge 14. The bracket 10 includes an upper end face, a lower end face, and a side wall connecting the upper and lower end faces. The lower end face is fixed to the mounting edge of the motion mechanism test piece 18 and has a through hole. One end of the simulated cylinder rod 9 passes through the through hole and connects to the linkage mechanism, while the other end connects to the force gauge 14. The actuating cylinder 11 is mounted on the outer side of the upper end face, and its actuating shaft passes through the upper end face and connects to the force gauge 14 via the force gauge adapter 13. The actuating end of the loading actuating cylinder assembly 16 has two ears 2, which are hinged to a single ear 1 via pins 4 and a pull rod ball 3. The single ear 1 is fixed to the actuator. The loading actuator cylinder assembly 16 has a loading force gauge 17, which enables the loading actuator cylinder assembly 16 to form a closed-loop control. The motion mechanism test piece 18 includes a guide vane adjustment mechanism, a nozzle adjustment mechanism, and a valve adjustment mechanism.

[0032] e) Step e: After the test officially begins, the time-varying load spectrum is applied to the actuator assembly 16 by controlling the loading force gauge 17. When the response time of the actuator 11 is consistent with that of the engine, the measured value of the force gauge 14 is the time-varying resistance force.

[0033] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A device for measuring the drag force of a motion mechanism of an aero-engine under load, used to test a motion mechanism test piece (18), the motion mechanism test piece (18) having multiple circumferentially distributed actuators and a linkage mechanism driven by the actuators, the linkage mechanism having an actuator that needs to overcome the load; Its features are, The measuring device includes: Base plate (7); A support cylinder (15) is installed on the base plate (7) to fix and support the test piece (18) of the motion mechanism; The lower support plate (6) is fixed on the base plate (7), and multiple circumferentially distributed actuating cylinder seats (8) are fixed on the lower support plate (6); Loading actuator assembly (16), the fixed end of the loading actuator assembly (16) is hinged to the actuator base (8), and the actuating end is hinged to the actuator of the motion mechanism test piece (18), for applying test load to the actuator; The loading simulation device includes: a bracket (10), a simulated cylinder rod (9), an actuator (11), a force gauge adapter (13), and a force gauge (14); The bracket (10) includes an upper end face, a lower end face, and a side wall connecting the upper end face and the lower end face. The lower end face is fixed on the mounting edge of the motion mechanism test piece (18). The lower end face has a through hole. One end of the simulated cylinder rod (9) passes through the through hole and is connected to the linkage mechanism. The other end is connected to the force gauge (14). The actuating cylinder (11) is installed on the outside of the upper end face. The actuating shaft of the actuating cylinder (11) passes through the upper end face and is connected to the force gauge (14) through the force gauge adapter (13).

2. The device for measuring the drag force of an aero-engine motion mechanism under load as described in claim 1, characterized in that, The actuating end of the loading actuator assembly (16) has two ears (2), which are hinged to a single ear (1) by a pin (4) and a pull rod ball (3), and the single ear (1) is fixed to the actuator.

3. The device for measuring the resistance force of an aero-engine motion mechanism under load as described in claim 1, characterized in that, The loading actuator cylinder assembly (16) has a loading force gauge (17), which enables the loading actuator cylinder assembly (16) to form a closed-loop control.

4. The device for measuring the resistance force of an aero-engine motion mechanism under load as described in claim 1, characterized in that, The motion mechanism test piece (18) includes a guide vane adjustment mechanism, a nozzle adjustment mechanism, and a valve adjustment mechanism.

5. A method for measuring the drag force of aero-engine motion mechanism under load, characterized in that, The test was conducted using the drag force measuring device for the motion mechanism of an aero-engine under load conditions as described in any one of claims 1-4, including: The finite element model of the motion mechanism test piece (18) was established using ANSYS to perform load equivalent analysis and obtain the equivalent concentrated force load under a single working condition. Load equivalent analysis was performed on different angles or displacements corresponding to multiple working conditions within the entire motion range. The equivalent concentrated force loads under different working conditions were fitted to form a time-varying load spectrum. By controlling the loading actuator assembly (16) to apply load to the actuator according to the time-varying load spectrum, the actuator (11) simulates the working mode of a real engine, and the measured value of the force gauge (14) is taken as the time-varying resistance force.

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