Blisk equivalent aeroelasticity test system

Abstract

The invention relates to a blisk equivalent aeroelasticity test system. The blisk equivalent aeroelasticity test system comprises a calculation-acquisition-control system and a vibration exciter-structure system, the calculation-acquisition-control system comprises an aerodynamic force calculation module, a data acquisition module and a centralized aerodynamic force loading control module; the vibration exciter-structure system comprises an eddy current displacement sensor and a test bed; the eddy current sensor collects displacement signals of specified collection points of all the blades in real time, converts the displacement signals into voltage signals and inputs the voltage signals into computer hardware of the aerodynamic force calculation module through a data transmission line. According to the method, a displacement acquisition and input-real-time calculation-aerodynamic force output system is constructed, displacement signals of all blades are acquired by utilizing an eddy current sensor, real-time aerodynamic force is calculated by utilizing real-time calculation hardware and an aerodynamic force reduced-order model, and the real-time aerodynamic force is output to a blisk through a vibration exciter; and equivalent simulation of the fluid-solid coupling effect of the blisk in the inner flow field is realized.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engine test equipment, in particular to an integral blade disk equivalent aeroelasticity test system. Background Art

[0002] Aircraft engines are developing towards higher thrust-to-weight ratios and higher loads, placing higher demands on the dynamic performance of their components. The blisk, a key load-bearing component within the engine, is also becoming more compact and lightweight to meet the higher performance requirements. Correspondingly, the lightweight design of the blisk makes the bidirectional fluid-structure coupling effect between it and the engine more significant, and its aeroelastic dynamics issues are becoming increasingly important. However, engine test runs are expensive, involve numerous interference factors, and it is difficult to obtain accurate dynamic information about the blisk. Therefore, building an equivalent aeroelastic test bench, using ground-based excitation equipment to simulate the flow field, and studying the aeroelastic dynamics of the blisk are of great significance for the early dynamic design and online health testing of the blisk.

[0003] Most early dynamic tests on blisks failed to consider bidirectional fluid-structure interaction. Instead, they focused on the blisks' structural dynamic characteristics, such as natural frequency, structural mode shapes, and modal damping ratios, and then incorporated these structural dynamic characteristics into aeroelastic analysis using fluid-structure decoupling. This analysis method can meet engineering accuracy requirements when the blisks have a high stiffness-to-mass ratio, but it can introduce significant errors as the blisks become increasingly flexible. Summary of the Invention

[0004] The present invention aims to solve the existing technical problems and proposes an equivalent aeroelastic test system for an integral blade disk. The present invention is achieved through the following technical solutions:

[0005] The present invention provides an integral blade equivalent aeroelasticity test system, comprising a calculation-acquisition-control system and an exciter-structure system;

[0006] The calculation-acquisition-control system includes an aerodynamic calculation module 1, a data acquisition module 2, and a centralized aerodynamic loading control module 3; the exciter-structure system includes an eddy current displacement sensor 5 and a test bench; the eddy current sensor 5 collects the displacement signal of the designated collection point of each blade in real time, converts the displacement signal into a voltage signal, and inputs it into the computer hardware of the aerodynamic calculation module 1 through a data transmission line.

[0007] Preferably, the aerodynamic force calculation module 1 calculates the real-time aerodynamic force based on the real-time displacement signal of the blade, converts it into a voltage signal, outputs it to the centralized aerodynamic force loading control module 3 through the data transmission line, and outputs the displacement signal and force signal of the blade through the data acquisition module 2.

[0008] Preferably, the test bench includes an upper cover of an integral blade disc test piece, an integral blade disc test piece 4, an upper cover 6 of the integral blade disc test piece, a lower base 7 of the integral blade disc, a test base 8, an exciter base 9a, an exciter base 9b, an exciter base 9c and an exciter 10; the integral blade disc test piece 4 is installed between the upper cover 6 of the integral blade disc test piece and the lower base 7 of the integral blade disc test piece by bolts, and the lower base 7 is installed on the test base 8 by a number of bolts.

[0009] Preferably, the eddy current displacement sensor 5 is fixed above the blade of the integral blade disk through a universal bracket, and the exciter 10 is fixed to the test base 8 through three fixed bases; the exciter base 9a is fixed to the base by bolts, and the exciter base 9b and the exciter base 9a are connected to their own slide rails by bolts; the exciter base 9c and the exciter base 9b are connected to their respective slide rails by bolts.

[0010] Preferably, the exciter 10 and the exciter base 9c are connected to the two concentric screw holes of the exciter base 9c by bolts; the exciter 10 and the integral blade disk test piece 4 are connected and fixed by a push rod and a nut, and the fixed position of the exciter 10 and the integral blade disk test piece 4 is the load point of the blade, and the position monitored by the eddy current displacement sensor is the monitoring point, and the positions of each load point and monitoring point coincide with each other.

[0011] Preferably, the blisk test piece 4 has a plurality of blades.

[0012] Preferably, a number of thin gaskets may be added between the lower base 7 and the integral blade disk test piece 4 to adjust the installation height of the integral blade disk test piece 4 .

[0013] Preferably, the vibrator bases 9a, 9b and 9c are provided with slide rails and concentric screw holes for adjusting the position and orientation, and the integral blade disk test piece is provided with holes at different positions.

[0014] Preferably, the displacement signals of the blades are collected by the same number of eddy current sensors 5 and input into the aerodynamic force calculation module 1 .

[0015] Preferably, the aerodynamic model in the aerodynamic calculation module 1 is obtained by an analytical or numerical theoretical method. The model takes the displacement of the entire blade as input and the aerodynamic force as output; the aerodynamic force acting on the blade is calculated by the real-time displacement of the blade, and after the calculation is completed, it is output to the centralized aerodynamic force loading control module.

[0016] Beneficial effects

[0017] The present invention constructs a displacement acquisition and input-real-time calculation-aerodynamic output system, uses eddy current sensors to collect displacement signals of all blades, uses real-time calculation hardware and an aerodynamic reduction model to calculate real-time aerodynamic force, and outputs it to the integral blade through an exciter, thereby achieving equivalent simulation of the fluid-solid coupling effect on the integral blade in the internal flow field.

[0018] The present invention allows precise adjustment of the exciter's mounting position and angle via the exciter base, thereby matching blades with different mounting angles and achieving excitation at different blade spans. Furthermore, the number of eddy current sensors and exciters can be adjusted accordingly to suit different blisk test specimens, enabling equivalent aeroelastic testing of blisk specimens of varying types and sizes.

[0019] The aerodynamic model in the aerodynamic calculation module of the present invention has a high degree of freedom. The aerodynamic model can be linear, nonlinear, or include independent aerodynamic forces that are unrelated to blade displacement. By changing the aerodynamic model in the aerodynamic calculation module, aeroelastic equivalent tests under different working conditions can be completed. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Fig. 1 Schematic diagram of the equivalent aeroelastic test system of the integral blade of the present invention.

[0021] Fig. 2 Schematic diagram of the aerodynamic calculation module 1 of the calculation-acquisition-control system (A) of the present invention.

[0022] Fig. 3 Schematic diagram of the excitation aerodynamic loading control system 3) and the exciter-structure system (B) of the present invention.

[0023] The parts are numbered as follows:

[0024] Computation-acquisition-control system (A), vibrator-structure system (B), aerodynamic calculation module 1, data acquisition module 2, centralized aerodynamic loading control module 3, integral blade disk test piece 4, eddy current displacement sensor 5, integral blade disk test piece upper cover 6, integral blade disk lower base 7, test base 8, vibrator base 9a, vibrator base 9b, vibrator base 9c, vibrator 10. DETAILED DESCRIPTION

[0025] The following is combined with Figs. 1 to 3 A specific embodiment of a rotating machinery test platform with adjustable mounting constraints of the present invention is further described in detail.

[0026] like Fig. 1 As shown, the integral blade equivalent aeroelasticity test system of the present invention includes a calculation-acquisition-control system (A) and an exciter-structure system (B).

[0027] The calculation-acquisition-control system includes an aerodynamic calculation module 1, a data acquisition module 2, and a centralized aerodynamic loading control module 3; the exciter-structure system includes an eddy current displacement sensor 5 and a test bench; the eddy current sensor 5 collects the displacement signal of the designated collection point of each blade in real time, converts the displacement signal into a voltage signal, and inputs it into the computer hardware of the aerodynamic calculation module 1 through a data transmission line.

[0028] The aerodynamic calculation module 1 calculates the real-time aerodynamic force based on the real-time displacement signal of the blade, converts it into a voltage signal, outputs it to the centralized aerodynamic loading control module 3 through the data transmission line, and outputs the displacement signal and force signal of the blade through the data acquisition module 2.

[0029] The test bench includes an upper cover of an integral blade disc test piece, an integral blade disc test piece 4, an upper cover 6 of the integral blade disc test piece, a lower base 7 of the integral blade disc, a test base 8, an exciter base 9a, an exciter base 9b, an exciter base 9c and an exciter 10; the integral blade disc test piece 4 is installed between the upper cover 6 of the integral blade disc test piece and the lower base 7 of the integral blade disc test piece by bolts, and the lower base 7 is installed on the test base 8 by several bolts, and the eddy current displacement sensor 5 is fixed above the blade of the integral blade disc through a universal bracket.

[0030] The vibrator 10 is fixed to the test base 8 through three fixed bases; the vibrator base 9a is fixed to the base by bolts, and the vibrator base 9b and the vibrator base 9a are connected to their own slide rails by bolts; the vibrator base 9c and the vibrator base 9b are connected to their respective slide rails by bolts.

[0031] The exciter 10 and the exciter base 9c are connected to the two concentric screw holes of the exciter base 9c by bolts; the exciter 10 and the integral blade disk test piece 4 are connected and fixed by a push rod and a nut. The fixed position of the exciter 10 and the integral blade disk test piece 4 is the load point of the blade, and the position monitored by the eddy current displacement sensor is the monitoring point. The positions of each load point and the monitoring point coincide with each other.

[0032] The blisk test piece 4 has a plurality of blades.

[0033] Several thin gaskets are added between the lower base 7 and the integral blade disk test piece 4 to adjust the installation height of the integral blade disk test piece 4.

[0034] The vibrator base 9a, the vibrator base 9b and the vibrator base 9c are provided with slide rails and concentric screw holes for adjusting the position and orientation, and the integral blade disk test piece is provided with holes at different positions.

[0035] The displacement signals of the blades are collected by the same number of eddy current sensors 5 and input into the aerodynamic force calculation module 1 .

[0036] The aerodynamic model in the aerodynamic calculation module 1 is obtained by an analytical or numerical theoretical method. The model takes the displacement of the entire blade as input and the aerodynamic force as output. The aerodynamic force acting on the blade is calculated by the real-time displacement of the blade and output to the centralized aerodynamic loading control module after the calculation is completed.

[0037] like Fig. 2 As shown, the displacement sensor inputs the displacement signal of the blade into the aerodynamic calculation module, and the aerodynamic calculation module outputs the aerodynamic signal to the centralized aerodynamic loading control module.

[0038] like Fig. 3 As shown in the figure, the centralized aerodynamic system receives the aerodynamic force signal output by the aerodynamic force calculation module as the reference force signal r, outputs the control output u through the feedforward compensator, and then inputs it into the power amplifier and exciter to complete the loading.

[0039] Example

[0040] In this embodiment, the calculation-acquisition-control system (A) and the exciter-structure system (B) are first installed. The number and specific installation positions of the exciters and eddy current sensors need to be determined according to the number of blades of the integral blade disk test piece. The exciter is connected to the integral blade disk test piece through a top rod and a nut. The excitation direction of the exciter needs to be consistent with the acquisition direction of the eddy current sensor.

[0041] Fig. 2 The aerodynamic model in the system takes the displacement of the blade as input and the aerodynamic force as output. The aerodynamic model is obtained through analytical methods (such as aerodynamic theory under various aerodynamic states) or numerical methods (computational fluid dynamics numerical simulation and power system identification technology), and then written into a computer program. The program is then loaded into the hardware system (semi-physical simulation hardware) of the time computing center.

[0042] Measure the dynamic characteristics of the power amplifier-exciter-blade system in a given frequency band, that is, the dynamic characteristics of the electromechanical coupling system with the voltage received by the power amplifier as input and the actual loading force as output, and use this to design Fig. 3 This process can be achieved by inputting a swept-frequency voltage signal of a given frequency band into the power amplifier, then collecting the output force signal of the exciter, and finally obtaining the dynamic characteristics of the system through system identification technology.

[0043] After completing the aerodynamic model loading and feedforward compensator design, the equivalent aeroelastic test of the integral blade disk was started. Fig. 1Connect the various hardware parts to each other, connect the eddy current displacement sensor to the computer hardware input port, connect the computer output port to the power amplifier, and connect the power amplifier to the exciter. Give the integral blade an initial excitation to force the blade to vibrate to generate an initial motion signal. The vibration displacement of the blade is collected by the eddy current sensor and input into the aerodynamic calculation module to calculate and output real-time aerodynamic force. Then, through the power amplifier and exciter, the aerodynamic force is concentratedly loaded on the designated load point of the blade, thereby realizing the fluid-solid coupling effect of the integral blade in a real engine. During the test, Fig. 1 The data acquisition system will collect the vibration displacement signal and exciter loading force signal of the integral blade during the entire test process. By analyzing the vibration signal of the integral blade, the dynamic characteristics of the integral blade under the action of fluid-solid coupling can be analyzed.

[0044] The above contents of the present invention are only preferred embodiments of the present invention and are not intended to limit the implementation scheme of the present invention. Ordinary technicians in this field can easily make corresponding changes or modifications based on the main concepts and spirit of the present invention. Therefore, the scope of protection of the present invention shall be based on the scope of protection required by the claims.

Claims

1. An equivalent aeroelastic test system for an integral blade, characterized in that: Including calculation-acquisition-control system and exciter-structure system; The calculation-acquisition-control system comprises an aerodynamic calculation module (1), a data acquisition module (2), and a centralized aerodynamic loading control module (3); the exciter-structure system comprises an eddy current displacement sensor (5) and a test bench; the eddy current sensor (5) collects displacement signals of designated acquisition points of each blade in real time, converts the displacement signals into voltage signals, and inputs the signals into the computer hardware of the aerodynamic calculation module (1) through a data transmission line.

2. The blisk equivalent aeroelasticity test system according to claim 1, characterized in that: The aerodynamic force calculation module (1) calculates the real-time aerodynamic force based on the real-time displacement signal of the blade, converts the calculated aerodynamic force into a voltage signal, outputs the calculated aerodynamic force to the centralized aerodynamic force loading control module (3) via a data transmission line, and outputs the displacement signal and force signal of the blade via a data acquisition module (2).

3. The blisk equivalent aeroelasticity test system according to claim 1, characterized in that: The test bench comprises an integral blade disc test piece upper cover, an integral blade disc test piece (4), an integral blade disc test piece upper cover (6), an integral blade disc lower base (7), a test base (8), an exciter base (9a), an exciter base (9b), an exciter base (9c), and an exciter (10); the integral blade disc test piece (4) is mounted between the integral blade disc test piece upper cover (6) and the integral blade disc test piece lower base (7) by bolts, the lower base (7) is mounted on the test base (8) by a plurality of bolts, and the eddy current displacement sensor (5) is fixed above the blades of the integral blade disc by a universal bracket.

4. The blisk equivalent aeroelasticity test system according to claim 3, characterized in that: The vibrator (10) is fixed on the test base (8) via three fixed bases; the vibrator base (9a) is fixed on the base via bolts; the vibrator base (9b) and the vibrator base (9a) are connected to their own slide rails via bolts; the vibrator base (9c) and the vibrator base (9b) are connected to their respective slide rails via bolts.

5. The blisk equivalent aeroelasticity test system according to claim 4, characterized in that: The exciter (10) and the exciter base (9c) are connected to two concentric screw holes of the exciter base (9c) by bolts; the exciter (10) and the integral blade disk test piece (4) are connected and fixed by a push rod and a nut; the fixed position of the exciter (10) and the integral blade disk test piece (4) is the load point of the blade, and the position monitored by the eddy current displacement sensor is the monitoring point, and the positions of each load point and the monitoring point coincide with each other.

6. The blisk equivalent aeroelasticity test system according to claim 2, characterized in that: The blisk test piece (4) has a plurality of blades.

7. The blisk equivalent aeroelasticity test system according to claim 2, characterized in that: A number of thin gaskets are added between the lower base (7) and the integral blade disc test piece (4) to adjust the installation height of the integral blade disc test piece (4).

8. The blisk equivalent aeroelasticity test system according to claim 2, characterized in that: The vibrator base (9a), the vibrator base (9b), and the vibrator base (9c) are provided with slide rails and concentric screw holes for adjusting positions and orientations, and the integral blade disk test piece is provided with holes at different positions.

9. The blisk equivalent aeroelasticity test system according to claim 6, characterized in that: The displacement signals of the blades are collected by the same number of eddy current sensors (5) and input into the aerodynamic force calculation module (1).

10. According to the integral blade equivalent aeroelastic test system of claim 1, the aerodynamic model in the aerodynamic calculation module (1) is obtained by an analytical or numerical theoretical method, the model takes the displacement of the integral blade as input and the aerodynamic force as output; the aerodynamic force acting on the blade is calculated by the real-time displacement of the blade, and after the calculation is completed, it is output to the centralized aerodynamic force loading control module.

Images