Compressor test verification method

Abstract

This invention discloses a compressor testing and verification method, which includes: a flow field boundary simulation step: changing the flow field temperature, pressure, inlet and outlet parameters, and airflow parameters of the compressor testing device to simulate the parameters of the overall compressor flow field, where the flow field boundary includes the inlet flow field and the outlet flow field; a thermal temperature field simulation step: connecting a heating device to the heated component of the compressor testing device to simulate the thermal temperature field of the overall compressor; a physical hardware simulation step: the parameters of the support frame and the supporting components in the compressor testing device are the same as those in the overall compressor to simulate the physical state of the overall compressor flow field; and a measurement hardware simulation step: the parameters of the sensors in the compressor testing device are the same as those in the overall compressor. Using this structure, the overall compressor verification stage is eliminated, improving verification efficiency and reducing verification risks and costs.

Description

Technical Field

[0001] This invention relates to a compressor testing and verification method. Background Technology

[0002] Currently, due to testing, manufacturing, and assembly reasons, the compressor body of multi-stage axial compressor test specimens for aero-engines both domestically and internationally often adopts different structural forms or boundary conditions than the compressor components. Because of these differences in structure and boundary conditions, the performance verified by the test specimens differs from the performance of the compressor components under the actual operating conditions of the entire engine (compressor inlet flow field versus booster stage outlet flow field). This leads to situations where the compressor performance verification by the test specimens meets the standards, but the compressor components fail to meet the standards when operating in the entire engine. Furthermore, for newly developed aero-engines, various boundary exploration tests are required. These tests may cause the compressor to approach a surge state, resulting in localized structural damage and affecting the safe operation of the entire engine. Because the compressor components and compressor performance test pieces have different structural forms, the structural strength problems identified when conducting near-surge tests on the compressor performance test pieces cannot be extrapolated to the compressor components working in the whole machine. This poses a hidden danger to the safe operation of the whole machine. Furthermore, important structural parameters obtained from the compressor performance test pieces, such as rotor blade tip clearance and grate tooth clearance, cannot be applied to the whole machine, increasing the cost of exploring important structural parameters of compressor components in the whole machine test. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to overcome the shortcomings of the existing technology, which is that the compressor test device cannot be applied to the compressor components working in the whole machine, thus posing a hidden danger to the safe operation of the whole machine and increasing the cost of exploring the important structural parameters of the compressor components in the whole machine test. The present invention provides a compressor test verification method.

[0004] The present invention solves the above-mentioned technical problems through the following technical solution:

[0005] This invention discloses a compressor testing and verification method, which includes: a flow field boundary simulation step: changing the flow field temperature, pressure, inlet and outlet parameters, and airflow parameters of the compressor testing device to simulate the parameters of the flow field of the entire compressor, wherein the flow field boundary includes the inlet flow field and the outlet flow field; a thermal temperature field simulation step: connecting a heating device to the heated component of the compressor testing device to simulate the thermal temperature field of the entire compressor; a physical hardware simulation step: the parameters of the support frame and the support components supporting the support frame in the compressor testing device are the same as the parameters of the support frame and the support components in the entire compressor to simulate the physical state of the flow field of the entire compressor; and a measurement hardware simulation step: the parameters of the sensors in the compressor testing device are the same as the parameters of the sensors in the entire compressor.

[0006] In this scheme, by adopting the above-mentioned structural form, the compressor test verification method can more accurately verify the compressor aerodynamic performance and effectively verify the functional realization effect of the compressor structure. At the same time, the more similar simulated dangerous subject test allows the verification content that needs to be completed at the compressor component level to be completed in the compressor performance test, without being carried over to the whole machine verification stage, which greatly improves the verification efficiency and reduces the verification risk and cost.

[0007] Preferably, in the step of simulating the flow field boundary, the airflow parameters include the inlet velocity and the airflow angle. The inlet velocity is adjusted by adjusting the opening of the throttle valve located on the test bench. The airflow angle is related to the flow field temperature, the pressure, and the inlet and outlet parameters.

[0008] In this design, the inlet flow rate can be altered by changing the opening of the throttle valve on the test bench, making the gas flow rate at the inlet of the compressor test device closer to that of the entire compressor. Furthermore, by controlling the flow field temperature, pressure, and inlet / outlet parameters, the airflow angles at the inlet and outlet of the compressor test device are made identical to those at the inlet and outlet of the entire compressor. This structural approach improves the accuracy of the compressor test device in simulating the operating environment of the entire compressor.

[0009] Preferably, in the step of simulating the flow field boundary, the airflow parameters also include the outlet velocity. A simulated combustion chamber structure is set in the compressor test device to simulate the temperature, pressure and outlet velocity of the compressor outlet of the whole machine.

[0010] Preferably, in the step of simulating the flow field boundary, an bleed valve is set at the bleed boundary of the compressor test device, and the flow field boundary of the bleed boundary conditions in the whole compressor is simulated by changing the opening degree of the bleed valve.

[0011] In this scheme, by adopting the above-mentioned structural form, the flow field boundary of the compressor bleed boundary conditions can be simulated by changing the opening degree of the bleed valve.

[0012] Preferably, in the step of simulating the flow field boundary, the inlet and outlet parameters include the inlet and outlet flow channel roughness and the inlet and outlet boundary layer thickness.

[0013] Preferably, in the step of simulating the thermal temperature field, the heating device is in contact with the outer wall of the heated component, and the heated component includes an inlet structure, a test specimen body stator, and an outlet structure.

[0014] In this scheme, by adopting the above-mentioned structural form, the thermal temperature field of the components in the compressor of the whole machine can be simulated through heat conduction and heat radiation.

[0015] Preferably, in the physical hardware simulation step, the parameters of the support frame include the size, stiffness, and material of the support frame;

[0016] And / or, the parameters of the support include the support model, the span of the support point, and the stiffness of the support point.

[0017] In this scheme, the above-mentioned structural form can simulate the physical state of the whole machine compressor.

[0018] Preferably, in the simulation measurement hardware step, the parameters of the sensor include the type, location, and number of sensors.

[0019] In this scheme, the above-mentioned structural form can ensure the consistency of data on flow field, temperature, and vibration.

[0020] The positive and progressive effects of this invention are as follows:

[0021] The compressor testing and verification method can more accurately verify the compressor's aerodynamic performance and effectively verify the functional realization of the compressor structure. At the same time, the more similar simulated hazardous subject tests allow the verification content that needs to be completed at the compressor component level to be completed in the compressor performance test, without being carried over to the whole machine verification stage. This greatly improves verification efficiency and reduces verification risks and costs. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the compressor test verification method according to an embodiment of the present invention;

[0023] Figure 2 This is a three-dimensional schematic diagram of the compressor testing apparatus according to an embodiment of the present invention;

[0024] Figure 3 This is a partial schematic diagram of the compressor test apparatus according to an embodiment of the present invention;

[0025] Figure 4This is a partial structural schematic diagram of the compressor test device according to an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the compressor testing device according to an embodiment of the present invention;

[0027] Figure 6 This is a schematic diagram of a compressor testing apparatus according to an embodiment of the present invention.

[0028] Explanation of reference numerals in the attached figures:

[0029] Imported Structure 1

[0030] Test piece body stator 2

[0031] Test piece body rotor 3

[0032] Front support 4

[0033] Rear support 5

[0034] Export Structure 6

[0035] Flow field generation ring 7

[0036] Heated component 8

[0037] Heating device 9

[0038] Compressor test apparatus 100 Detailed Implementation

[0039] The present invention will be further illustrated by way of embodiments below, but the present invention is not limited to the scope of the embodiments.

[0040] This invention discloses a compressor testing and verification method to address the problem that the compressor testing device 100 cannot be extrapolated to the compressor components working in the whole machine, which in turn poses a hidden danger to the safe operation of the whole machine and reduces the cost of exploring important structural parameters of compressor components in the whole machine test.

[0041] like Figures 1 to 6 As shown, the compressor test verification method includes: Simulating flow field boundary steps: changing the flow field temperature, pressure, inlet and outlet parameters, and airflow parameters of the compressor test device 100 to simulate the parameters of the flow field of the entire compressor, where the flow field boundary includes the inlet flow field and the outlet flow field; Simulating thermal temperature field steps: connecting the heating device 9 to the heating element 8 of the compressor test device 100 to simulate the thermal temperature field of the entire compressor; Simulating physical hardware steps: the parameters of the support frame and the supporting elements in the compressor test device 100 are the same as the parameters of the support frame and supporting elements in the entire compressor to simulate the physical state of the flow field of the entire compressor; Simulating measurement hardware steps: the parameters of the sensors in the compressor test device 100 are the same as the parameters of the sensors in the entire compressor.

[0042] In practical applications, for the step of simulating flow field boundaries, it is necessary to clearly define the boundary conditions of the compressor inlet flow field, the outlet flow field boundary, and the boundary conditions of various induced draft air fields. For the step of simulating the thermal temperature field, it is necessary to clearly define the thermal temperature field of the compressor components in the entire aero-engine. For the step of simulating physical hardware, it is necessary to clearly define that the compressor test device 100 adopts the high-pressure "rotor-support" layout and structural parameters (such as bearing selection, thrust bearing position, support span, support stiffness, etc.) of the entire aero-engine so that the compressor rotor part of the compressor test device 100 can simulate the dynamic characteristics of the high-pressure rotor (compressor rotor part) of the entire aero-engine. In addition, it is necessary to clearly define that the compressor part structure and structural characteristic parameters (such as rotor tip clearance, grate tooth clearance) of the compressor test device 100 are completely consistent with the high-pressure compressor components in the entire aero-engine. For the simulation measurement hardware steps, it is ensured that the compressor test device 100 and the compressor components in the aircraft engine have completely identical measurement points in terms of flow field, temperature field, and vibration, and the sensor models are also completely identical. Using this structural form, the compressor test verification method can more accurately verify the compressor's aerodynamic performance and effectively verify the functional realization of the compressor structure. Furthermore, the more similar simulation of hazardous subject tests allows verification content that would otherwise need to be completed at the compressor component level to be completed within the compressor performance test, eliminating its need to be carried over to the overall engine verification stage. This significantly improves verification efficiency and reduces verification risks and costs.

[0043] In the simulated flow field boundary step, the airflow parameters include the inlet velocity and the airflow angle. The inlet velocity is adjusted by regulating the opening of the throttle valve located on the test bench. The airflow angle is related to the flow field temperature, pressure, and inlet / outlet parameters. Specifically, an bleed valve is arranged between the compressor test device 100 and the test bench. By changing the opening of the bleed valve, a flow field boundary simulating the bleed boundary conditions of the compressor in an aero-engine can be obtained. Furthermore, the compressor test device 100 works in conjunction with the test bench. By changing the opening of the throttle valve on the test bench, a flow field simulating the Reynolds number at the compressor inlet of an aero-engine can be obtained. By controlling the flow field temperature, pressure, and inlet / outlet parameters, the airflow angles at the inlet and outlet of the compressor test device 100 are made the same as those at the inlet and outlet of the entire aero-engine compressor. This structural design improves the accuracy of the compressor test device 100 in simulating the operating environment of the entire aero-engine compressor.

[0044] In practical application, a flow field generating ring 7 is arranged at the inlet of the compressor test device 100 to obtain a profile simulating the total temperature, total pressure, and airflow velocity at the compressor inlet of an aero-engine. In this embodiment, the flow field generating ring 7 is a grid distortion generator. In other embodiments, the type of flow field generating ring 7 is not limited.

[0045] In the simulated flow field boundary step, the airflow parameters also include the outlet velocity. A simulated combustion chamber structure is set in the compressor test device 100 to simulate the temperature, pressure, and outlet velocity of the entire compressor. Specifically, simulated combustion chamber structural features are arranged at the outlet of the compressor test device 100 to obtain a simulated profile of total temperature, total pressure, and airflow velocity at the outlet of the entire compressor.

[0046] In the step of simulating the flow field boundary, an bleed valve is installed at the bleed boundary of the compressor test device 100. By changing the opening degree of the bleed valve, the flow field boundary of the bleed boundary conditions in the whole compressor is simulated. Using the above structural form, the flow field boundary of the bleed boundary conditions of the whole compressor can be simulated by changing the opening degree of the bleed valve.

[0047] In the simulated flow field boundary step, the inlet and outlet parameters include the roughness of the inlet and outlet flow channels and the thickness of the inlet and outlet boundary layer. Specifically, by increasing the roughness of the inlet flow channel of the compressor test device 100, a flow field that can simulate the boundary layer thickness at the compressor inlet of an aircraft engine is obtained.

[0048] In the simulated thermal temperature field step, the heating device 9 is attached to the outer wall of the heated component 8, which includes an inlet structure 1, a test component stator 2, and an outlet structure 6. Specifically, in the "rotor-support" section of the compressor test device 100, a simulated high-pressure rotor support frame structure for an aero-engine is adopted, using the same bearing selection, thrust bearing position, support span, support stiffness, and other structural and characteristic parameters. Furthermore, the compressor body section of the compressor test device 100 adopts the same structure as the compressor components in an aero-engine. Additionally, using the above structural form, heating devices 9 are arranged around the compressor body section of the compressor test device 100 on the inlet and outlet load-bearing frames. That is, heat is transferred to the compressor test device 100 through heat conduction and radiation to simulate the thermal temperature field of the compressor components in an aero-engine. Specifically, the heating device 9 includes multiple heating wires and an annular heater housing. The multiple heating wires are circumferentially spaced around the outer and inner walls of the heated component 8, and the inner wall of the annular heater housing is in contact with the outer wall of the heated component 8.

[0049] In practical use, the parameters of the support frame include the size, stiffness and material of the support frame; the parameters of the support component include the model of the support component, the span of the support point and the stiffness of the support point, so as to simulate the physical state of the whole compressor.

[0050] In this embodiment, the heating device 9 can be an electric heating device. In other embodiments, the type of heating device 9 is not limited.

[0051] In the hardware simulation measurement steps, the sensor parameters include the sensor type, location, and quantity. Specifically, the compressor test apparatus 100 arranges measurement points for flow field, temperature field, and vibration that are completely identical in type, location, and quantity to those of the compressor components in the aircraft engine, and the sensor models are completely identical. This structural approach ensures the consistency of data regarding flow field, temperature, and vibration.

[0052] In practical implementation, the compressor test device 100 typically includes an inlet structure 1, a test specimen stator 2, a test specimen rotor 3, a front support 4, a rear support 5, and an outlet structure 6. Due to testing, manufacturing, and assembly reasons, the compressor body of the multi-stage axial flow compressor test device 100 for domestic and international aero-engines often adopts a different structural form or boundary condition form than the compressor components. This leads to problems such as inconsistencies between the performance of the compressor test device 100 and the performance of the compressor components during overall engine operation, the inability to extrapolate structural strength issues identified in the performance test specimen to the compressor components operating in the overall engine, and the inability to apply important structural parameters (such as rotor tip clearance and grate clearance) obtained by the compressor test device 100 to the overall engine. Adopting the aforementioned structural form allows for consideration throughout the entire design, manufacturing, and testing cycle, enabling the design to fully consider flow field boundaries, thermal temperature fields, physical hardware, and measurement hardware, thus more accurately simulating the overall engine operating environment.

[0053] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A compressor test verification method, characterized in that, The compressor testing and verification method includes: Simulated flow field boundary steps: Change the flow field temperature, pressure, inlet and outlet parameters, and airflow parameters of the compressor test device to simulate the parameters of the whole compressor flow field. The flow field boundary includes the inlet flow field and the outlet flow field. Simulated thermal temperature field steps: Connect the heating device to the heated component of the compressor test device to simulate the thermal temperature field of the whole compressor; Simulated physical hardware steps: The parameters of the support frame and the support components supporting the support frame in the compressor test device are the same as the parameters of the support frame and the support components in the whole compressor, so as to simulate the physical state of the flow field of the whole compressor. Simulation measurement hardware steps: The parameters of the sensors in the compressor test device are the same as the parameters of the sensors in the complete compressor.

2. The compressor test verification method as described in claim 1, characterized in that, In the simulated flow field boundary step, the airflow parameters include the inlet velocity and the airflow angle. The inlet velocity is adjusted by adjusting the opening of the throttle valve on the test bench. The airflow angle is related to the flow field temperature, the pressure, and the inlet and outlet parameters.

3. The compressor test verification method as described in claim 1, characterized in that, In the step of simulating the flow field boundary, the airflow parameters also include the outlet velocity. A simulated combustion chamber structure is set in the compressor test device to simulate the temperature, pressure and outlet velocity of the compressor outlet of the whole machine.

4. The compressor test verification method as described in claim 1, characterized in that, In the step of simulating the flow field boundary, an bleed valve is set at the bleed boundary of the compressor test device, and the flow field boundary of the bleed boundary conditions in the whole compressor is simulated by changing the opening degree of the bleed valve.

5. The compressor test verification method as described in claim 1, characterized in that, In the simulated flow field boundary step, the inlet and outlet parameters include the inlet and outlet flow channel roughness and the inlet and outlet boundary layer thickness.

6. The compressor test verification method as described in claim 1, characterized in that, In the simulated thermal temperature field step, the heating device is attached to the outer wall of the heated component, which includes an inlet structure, a test specimen body stator, and an outlet structure.

7. The compressor test verification method as described in claim 1, characterized in that, In the simulated physical hardware steps, the parameters of the support frame include the size, stiffness, and material of the support frame; And / or, the parameters of the support include the support model, the span of the support point, and the stiffness of the support point.

8. The compressor test verification method as described in claim 1, characterized in that, In the simulation measurement hardware steps, the parameters of the sensor include the type, location, and number of sensors.

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