A method for regulating the bypass ratio under the conditions of a whole simulated turbofan engine

Abstract

The present application provides a method for regulating the bypass ratio under the conditions of a whole turbofan engine, which is realized based on a twin-spool compressor tester and belongs to the field of aeroengine tests. The method includes: determining the control parameters under the whole-engine state; determining the control accuracy of the test state control parameters of the twin-spool compressor tester; constructing a control module which stores the regulation law under the whole-engine state and is used to make the speeds of the fan and the high-pressure compressor in a linkage mode during the test; monitoring the bypass throttle valve for regulating the fan pressure ratio, then regulating the core throttle valve while monitoring the high-pressure compressor pressure ratio, and finally regulating the core throttle valve and the bypass throttle valve simultaneously to make the high-pressure compressor pressure ratio and the fan pressure ratio meet the requirements; keeping the state of the twin-spool compressor tester stable and collecting the compressor parameters through the inner and outer bypass exhaust gas collection device; regulating the speed of the high-pressure compressor or the fan speed according to the speed difference between the fan and the high-pressure compressor under the whole-engine state, and collecting the compressor parameters after stabilization.

Description

Technical Field

[0001] This application belongs to the field of aero-engines, and particularly relates to a method for regulating the bypass ratio under the conditions of simulating a whole turbofan engine. Background Technique

[0002] The bypass ratio is a key parameter of a turbofan engine, and its definition is the ratio of the airflow rate flowing into the outer bypass duct of the engine to the airflow rate flowing into the inner bypass duct. The bypass ratio has a great influence on the performance of the turbofan engine, such as thrust, fuel efficiency, and noise. During the whole-engine test of the turbofan engine, due to structural limitations, currently, only the total airflow rate flowing into the turbofan engine can be measured at the inlet of the turbofan engine, and the real-time measurement of the bypass ratio cannot be achieved, and the bypass ratio under the working environment of the whole turbofan engine cannot be obtained.

[0003] Although there are methods for regulating the bypass ratio of a single-spool compressor in the prior art, since the single-spool compressor has only one rotating shaft and lacks a part of the compression system compared with the whole turbofan engine, the structural form and working mode of the single-spool compressor are quite different from those of the whole turbofan engine, and it cannot simulate the real working environment and working state of the whole turbofan engine and cannot directly provide data support for the development of the whole turbofan engine in terms of the bypass ratio. Summary of the Invention

[0004] The purpose of this application is to provide a method for regulating the bypass ratio under the conditions of simulating a whole turbofan engine to solve or alleviate at least one problem in the background technique.

[0005] The technical solution of this application is: A method for regulating the bypass ratio under the conditions of simulating a whole turbofan engine, which is realized based on a two-spool compressor tester, and the method includes:

[0006] Determine the control parameters in the whole-engine state, and the control parameters include the rotational speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment law, the high-pressure compressor blade angle adjustment law, the fan operating point pressure ratio, and the high-pressure compressor operating point pressure ratio;

[0007] Determine the control accuracy of the control parameters in the test state of the two-spool compressor tester;

[0008] Construct a control module, which stores the rotational speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment law, and the high-pressure compressor blade angle adjustment law in the whole-engine state, and is used to make the rotational speeds of the fan and the high-pressure compressor in a linkage mode during the test;

[0009] Monitor the fan pressure ratio, adjust the outer throttle valve, make the fan pressure ratio the same or similar to that of the whole machine, then adjust the inner throttle valve, monitor the high-pressure compressor pressure ratio at the same time, make the high-pressure compressor pressure ratio the same or similar to that of the whole machine, and then adjust the inner throttle valve and the outer throttle valve at the same time, so that the high-pressure compressor pressure ratio and the fan pressure ratio meet the control accuracy requirements;

[0010] Keep the state of the biaxial compressor tester stable, collect compressor parameters through the outer exhaust collection device and the inner exhaust collection device of the biaxial compressor tester, the compressor parameters include fan and high-pressure compressor flow, pressure ratio, efficiency, blade angle and bypass ratio, and the stable state is used as the basic state design point of the inner and outer rotor variable speed difference test;

[0011] According to the fan and high-pressure compressor speed difference requirements under the whole machine state, the high-pressure compressor speed or fan speed is adjusted according to the preset speed interval. When the high-pressure compressor speed and the fan speed are stable, the compressor parameters are collected, and then the next fan and high-pressure compressor speed difference adjustment and compressor parameters collection are carried out.

[0012] Preferably, determining the control accuracy of the test state control parameters of the biaxial compressor tester includes:

[0013] The control accuracy of the converted speed of the fan and high-pressure compressor is determined to be 0.2%, the adjustment accuracy of the blade angle of the fan and high-pressure compressor is 0.5°, and the control accuracy of the pressure ratio of the fan and high-pressure compressor is 0.3%.

[0014] Preferably, when the fan and the high-pressure compressor reach the target rotational speeds, the linkage relationship between the rotational speeds of the fan and the high-pressure compressor is released.

[0015] Preferably, the same or similar means that the fan pressure ratio or the high-pressure compressor pressure ratio is no more than 10% of the corresponding pressure ratio under the whole machine state.

[0016] Preferably, the predetermined rotation speed interval does not exceed 100 rpm.

[0017] In the second aspect, the technical solution provided by the present application is: a method for regulating the bypass ratio under the condition of simulating a complete turbofan engine, which is implemented based on a dual-axis compressor tester, and the method comprises:

[0018] Determine the control parameters under the whole machine state, the control parameters include the speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment law, the high-pressure compressor blade angle adjustment law, the fan operating point pressure ratio, and the high-pressure compressor operating point pressure ratio;

[0019] Determine the control accuracy of the test state control parameters of the biaxial compressor tester;

[0020] Build a control module which stores the rotational speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment law, and the high-pressure compressor blade angle adjustment law under the whole-machine state, and is used to make the rotational speeds of the fan and the high-pressure compressor in a linkage mode during the test process;

[0021] Monitor the fan pressure ratio, adjust the bypass throttle valve to make the fan pressure ratio the same as or close to that in the whole-machine state, and then adjust the core throttle valve. At the same time, monitor the high-pressure compressor pressure ratio to make the high-pressure compressor pressure ratio the same as or close to that in the whole-machine state. Then, adjust the core throttle valve and the bypass throttle valve simultaneously to make the high-pressure compressor pressure ratio and the fan pressure ratio meet the control accuracy requirements;

[0022] Keep the state of the twin-spool compressor tester stable, and collect compressor parameters through the bypass exhaust gas collection device and the core exhaust gas collection device of the twin-spool compressor tester. The compressor parameters include the flow rate, pressure ratio, efficiency, blade angle, and bypass ratio of the fan and the high-pressure compressor. The stable state is the basic state design point when changing the turbine nozzle area or adjusting the tailpipe nozzle area;

[0023] According to the fan pressure ratio and the high-pressure compressor pressure ratio after adjusting the turbine nozzle area or the tailpipe nozzle area, adjust the core throttle valve and the bypass throttle valve simultaneously to make the fan pressure ratio and the high-pressure compressor pressure ratio the same as those in the whole-machine state. After the state point is stable, collect the compressor parameters.

[0024] Preferably, determining the control accuracy of the test state control parameters of the twin-spool compressor tester includes:

[0025] Determine that the control accuracy of the corrected rotational speed of the fan and the high-pressure compressor is 0.2%, the adjustment accuracy of the fan and high-pressure compressor blade angles is 0.5°, and the control accuracy of the fan and high-pressure compressor pressure ratios is 0.3%.

[0026] Preferably, the "same as or close to" means that the fan pressure ratio or the high-pressure compressor pressure ratio does not exceed 10% of the corresponding pressure ratio in the whole-machine state.

[0027] The method of the present application can realize the bypass ratio adjustment under the simulated whole-machine environment, and the bypass ratio measurement can be realized by adjusting the bypass ratio alone or in combination through a variety of control means. There is no need to stop the machine for hardware adjustment, which can effectively improve the test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions provided by the present application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application.

[0029] Figure 1 It is a schematic structural diagram of the twin-spool compressor tester (part) in the present application.

[0030] Figure 2 This is a top view of the structure (partial) of the twin-spool compressor tester in this application. Specific implementation manners

[0031] To make the purpose, technical solutions, and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings in the embodiments of this application.

[0032] In order to simulate the working environment during the change process of the rotational speed difference between the inner and outer rotors in a whole turbofan engine and measure the overall bypass ratio of the whole engine in real time, or to simulate the working environment when changing the area of the turbine guide vane or adjusting the area of the tail nozzle in a whole turbofan engine and measure the overall bypass ratio of the whole engine in real time, this application proposes a bypass ratio control method for simulating the working environment of a whole turbofan engine based on a twin-spool compressor tester.

[0033] Combined with Figure 1 and Figure 2 As shown in the schematic diagram of the structure of the twin-spool compressor tester, the twin-spool compressor tester 100 includes a fan 10 (or a low-pressure compressor), an intermediate casing 20, an outer-duct exhaust collection device 30, a high-pressure compressor 40, an inner-duct exhaust collection device 50, a transmission shaft 60, a gearbox 70, and a driving device 80.

[0034] Among them, a fan blade angle adjustment system 11 is provided on the fan 10, which is connected to the fan 10 and is used to adjust and control the fan blade angle. A high-pressure blade angle adjustment system 41 is provided on the high-pressure compressor 40, which is connected to the high-pressure compressor 40 and is used to adjust and control the high-pressure compressor blade angle.

[0035] An outer-duct throttle valve 31 and an outer-duct flow measurement device 32 are respectively provided at the inlet end and the outlet end of the outer-duct exhaust collection device 30. The flow rate of the outer-duct exhaust collection device 30 can be adjusted through the outer-duct throttle valve 31, thereby controlling the fan operating point pressure ratio. The outer-duct exhaust flow rate can be measured through the outer-duct flow measurement device 32. An inner-duct throttle valve 51 and an inner-duct flow measurement device 52 are respectively provided at the inlet end and the outlet end of the inner-duct exhaust collection device 50. The flow rate of the inner-duct exhaust collection device 50 can be adjusted through the inner-duct throttle valve 51, thereby controlling the high-pressure compressor operating point pressure ratio. The inner-duct exhaust flow rate can be measured by the inner-duct flow measurement device 52.

[0036] In this embodiment of this application, the structures of the outer-duct exhaust collection device 30 and the inner-duct exhaust collection device 50 are the same or similar, and both are spiral volute structures.

[0037] The intermediate casing 20 is arranged between the fan 10 and the high-pressure compressor 40 and is used to form the inner and outer ducts. The outer-duct air flow flows through the intermediate casing 20 to the outer-duct exhaust collection device 30, and the inner-duct air flow flows to the inner-duct exhaust collection device 50 after passing through the high-pressure compressor 40.

[0038] The transmission shaft 60 includes a high-pressure shaft 61 and a low-pressure shaft 62. The high-pressure shaft 61 and the low-pressure shaft 62 are respectively connected to the high-pressure compressor 40 and the fan 10 to form inner and outer rotors, and the high-pressure shaft 61 and the low-pressure shaft 62 are connected to the gearbox 70.

[0039] The driving device 80 includes a first driving device 81 and a second driving device 82. Both the first driving device 81 and the second driving device 82 are connected to the gearbox 70, and respectively drive the high-pressure shaft 61 and the low-pressure shaft 62 to rotate through the gearbox 70, so as to realize the speed control of the fan 10 and the high-pressure compressor 40. In some embodiments of the present application, the driving device 80 is a driving motor. Among them, the driving motor can be a stepping motor or a servo motor in terms of type to improve its control accuracy.

[0040] Based on the above-mentioned dual-axis compressor tester 100, the present application provides a method for regulating the bypass ratio under the conditions of simulating a whole turbofan engine. The method includes: measuring the bypass ratio under different speed differences between the inner and outer rotors and measuring the bypass ratio by changing the turbine guide vane or adjusting the area of the tail nozzle.

[0041] I. The process of measuring the bypass ratio under different speed differences between the inner and outer rotors is as follows:

[0042] S11, determine the control parameters under the whole machine state. The control parameters include the speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment rule, the high-pressure compressor blade angle adjustment rule, the fan operating point pressure ratio, and the high-pressure compressor operating point pressure ratio.

[0043] S12, determine the control accuracy of the control parameters of the dual-axis compressor tester test state.

[0044] Since there is no test control requirement for regulating the bypass ratio by using a dual-axis compressor tester in the current existing technology, the present application determines, according to the single-axis compressor test standard and the dual-axis compressor test experience, that the control accuracy of the converted speeds of the fan and the high-pressure compressor is 0.2%, the control accuracy of the fan blade angle and the high-pressure compressor blade angle adjustment is 0.5°, and the control accuracy of the fan and the high-pressure compressor pressure ratio is 0.3%.

[0045] S13, construct a control module. The control module stores the speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment rule, the high-pressure compressor blade angle adjustment rule, etc. under the whole machine state, and is used to make the speeds of the fan and the high-pressure compressor in a linkage mode during the test process.

[0046] Before using the biaxial compressor tester 100 for testing, a control module is first constructed, and the matching relationship between the fan and high-pressure compressor speeds of the whole machine, the fan blade angle adjustment law, and the high-pressure compressor blade angle adjustment law are input into the control module. During the test, the control module only needs to control the high-pressure compressor speed to make each device or apparatus of the biaxial compressor tester 100 automatically operate according to the pre-input adjustment law. After reaching the target speed, the linkage relationship between the fan and high-pressure compressor speeds is released, and at this time, the high-pressure compressor speed and the fan speed can be adjusted arbitrarily without affecting each other.

[0047] S14, monitor the fan pressure ratio, adjust the outer throttle valve 31, make the fan pressure ratio the same or similar to that in the whole machine state, then adjust the inner throttle valve 51, and monitor the high-pressure compressor pressure ratio at the same time, make it the same or similar to that in the whole machine state, and then adjust the inner throttle valve 51 and the outer throttle valve 31 at the same time, so that the high-pressure compressor pressure ratio and the fan pressure ratio meet the control accuracy requirements.

[0048] In some embodiments of the present application, the fan pressure ratio or the high-pressure compressor pressure ratio can be regarded as the same or similar if it does not exceed 10% of the corresponding pressure ratio in the whole machine state.

[0049] S15, maintain the state of the biaxial compressor tester 100 stable, collect compressor parameters such as fan and high-pressure compressor flow, pressure ratio, efficiency, blade angle, bypass ratio, etc. through the outer exhaust gas collecting device 30 and the inner exhaust gas collecting device 50 of the biaxial compressor tester 100, and this stable state is used as the basic state design point for the inner and outer rotor variable speed difference test.

[0050] S16, according to the fan and high-pressure compressor speed difference requirement under the whole machine state, the high-pressure compressor speed or the fan speed is adjusted at a predetermined interval. When the high-pressure compressor speed and the fan speed are stable, the compressor parameters such as the fan and high-pressure compressor flow rate, pressure ratio, efficiency, blade angle, and bypass ratio are collected, and then the next adjustment of the fan and high-pressure compressor speed difference and the collection of compressor parameters are performed.

[0051] For example, in this embodiment of the present application, the slip change process under the whole machine state is that the fan speed remains different, and the high-pressure compressor speed difference varies within the range of ±200rpm of the basic state design point. Therefore, the basic state design point speed can be changed at a speed interval of +100rpm, +200rpm at 100rpm, or at a speed interval of -100rpm, -200rpm at the basic state design point speed. After reaching the target speed, it stays at each speed for 1 minute. After the state point stabilizes, the compressor parameters are collected according to the process of step S15.

[0052] 2. The bypass ratio measurement process when changing the turbine guide vane area or adjusting the tail nozzle area is as follows:

[0053] S21. Determine the control parameters in the whole - machine state. The control parameters include the rotational - speed matching relationship between the fan and the high - pressure compressor, the fan - blade angle adjustment law, the high - pressure - blade angle adjustment law, the fan operating - point pressure ratio, and the high - pressure - compressor operating - point pressure ratio.

[0054] S22. Determine the control accuracy of the state - control parameters during the test of the two - spool compressor tester.

[0055] In the prior art, there are no test - control requirements for regulating the bypass ratio using a two - spool compressor tester. According to the single - spool compressor test standard and the two - spool compressor test experience, in this application, the control accuracy of the fan corrected speed and the high - pressure - compressor corrected speed is determined to be 0.2%, the adjustment accuracy of the fan and high - pressure - compressor blade angles is 0.5°, and the control accuracy of the fan and high - pressure - compressor pressure ratios is 0.3%.

[0056] S23. Construct a control module. The control module stores the rotational - speed matching relationship between the fan and the high - pressure compressor, the fan - blade angle adjustment law, the high - pressure - blade angle adjustment law, etc. in the whole - machine state, and is used to keep the rotational speeds of the fan and the high - pressure compressor in a linkage mode during the test process.

[0057] Before conducting the test using the two - spool compressor tester 100, first construct a control module. Input the rotational - speed matching relationship between the fan and the high - pressure compressor, the fan - blade angle adjustment law, and the high - pressure - blade angle adjustment law in the whole - machine state into the control module. During the test process, by controlling the rotational speed of the high - pressure compressor, each device or apparatus of the two - spool compressor tester 100 can automatically operate according to the pre - input control law, and after reaching the target rotational speed, keep the rotational speeds of the fan and the high - pressure compressor unchanged.

[0058] S24. Monitor the fan pressure ratio, adjust the bypass throttle valve 31 to make the fan pressure ratio the same as or close to that in the whole - machine state; then adjust the core throttle valve 51, while monitoring the high - pressure - compressor pressure ratio to make it the same as or close to that in the whole - machine state, and then adjust the core throttle valve 51 and the bypass throttle valve 31 simultaneously to make the high - pressure - compressor and fan pressure ratios meet the control - accuracy requirements.

[0059] In some embodiments of this application, if the fan pressure ratio or the high - pressure - compressor pressure ratio does not exceed 10% of its corresponding pressure ratio in the whole - machine state, it can be regarded as the same as or close to it.

[0060] S25. Keep the state of the two - spool compressor tester 100 stable, and collect compressor parameters such as the flow rate, pressure ratio, efficiency, blade angle, bypass ratio of the fan and the high - pressure compressor through the bypass exhaust - gas collection device 30 and the core exhaust - gas collection device 50 of the two - spool compressor tester 100. This stable state is used as the basic - state design point when changing the turbine - nozzle area or adjusting the afterburner - nozzle area.

[0061] S26. Adjust the fan pressure ratio and the high-pressure compressor pressure ratio according to the turbine guide vane area or the nozzle area, and at the same time adjust the core throttle valve 51 and the bypass throttle valve 31 to make the fan pressure ratio and the high-pressure compressor pressure ratio the same as those in the whole engine state. After the state point is stable, collect the compressor parameters such as the flow rate, pressure ratio, efficiency, blade angle, and bypass ratio of the fan and the high-pressure compressor.

[0062] For example, in this embodiment of the present application, when adjusting the core throttle valve 51 and the bypass throttle valve 31 at the same time to make the fan pressure ratio and the high-pressure compressor pressure ratio the same as those in the whole engine state, the control accuracy requirements must also be met. During the process of adjusting different pressure ratios, the state point stays for 1 minute after stabilization. After the state point is stable, collect the compressor parameters such as the flow rate, pressure ratio, efficiency, blade angle, and bypass ratio of the fan and the high-pressure compressor according to step S25.

[0063] The structural form of the dual-axis compressor tester 100 in the present application is the same as that of the whole turbofan engine, which can ensure the same hardware environment. During the test using the dual-axis compressor tester 100, its bypass ratio is the ratio of the flow rate measured by the bypass exhaust collection device 50 to the flow rate measured by the core exhaust collection device 30. The layout of the inner and outer bypass exhaust collection devices can be carried out according to relevant standards. The core flow rate can also be obtained by subtracting the bypass flow rate from the total inlet flow rate. The method of the present application can realize the bypass ratio adjustment under the simulated whole engine environment, and the bypass ratio measurement can be realized by individually adjusting or combining various control means to adjust the bypass ratio, without stopping the engine for hardware adjustment, which can effectively improve the test efficiency.

[0064] The above is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claimed rights.

Claims

1. A method for regulating bypass ratio under the condition of simulating a complete turbofan engine, characterized in that: Based on a biaxial compressor tester, the method comprises: Determine the control parameters under the whole machine state, the control parameters include the speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment law, the high-pressure compressor blade angle adjustment law, the fan operating point pressure ratio, and the high-pressure compressor operating point pressure ratio; Determine the control accuracy of the test state control parameters of the biaxial compressor tester; Constructing a control module, which stores the speed matching relationship of the fan and the high-pressure compressor in the whole machine state, the fan blade angle adjustment law and the high-pressure compressor blade angle adjustment law, and is used to make the speeds of the fan and the high-pressure compressor in a linkage mode during the test; Monitor the fan pressure ratio, adjust the outer throttle valve, make the fan pressure ratio the same or similar to that of the whole machine, then adjust the inner throttle valve, monitor the high-pressure compressor pressure ratio at the same time, make the high-pressure compressor pressure ratio the same or similar to that of the whole machine, and then adjust the inner throttle valve and the outer throttle valve at the same time, so that the high-pressure compressor pressure ratio and the fan pressure ratio meet the control accuracy requirements; Keep the state of the biaxial compressor tester stable, collect compressor parameters through the outer exhaust collection device and the inner exhaust collection device of the biaxial compressor tester, the compressor parameters include fan and high-pressure compressor flow, pressure ratio, efficiency, blade angle and bypass ratio, and the stable state is used as the basic state design point of the inner and outer rotor variable speed difference test; According to the fan and high-pressure compressor speed difference requirements under the whole machine state, the high-pressure compressor speed or fan speed is adjusted according to the preset speed interval. When the high-pressure compressor speed and the fan speed are stable, the compressor parameters are collected, and then the next fan and high-pressure compressor speed difference adjustment and compressor parameters collection are carried out.

2. The bypass ratio control method under the condition of simulating a complete turbofan engine according to claim 1, characterized in that: Determine the control accuracy of the test state control parameters of the biaxial compressor tester including: The control accuracy of the converted speed of the fan and high-pressure compressor is determined to be 0.2%, the adjustment accuracy of the blade angle of the fan and high-pressure compressor is 0.5°, and the control accuracy of the pressure ratio of the fan and high-pressure compressor is 0.3%.

3. The bypass ratio control method under the condition of simulating a complete turbofan engine according to claim 1, characterized in that: When the fan and the high-pressure compressor reach the target rotational speeds, the linkage relationship between the fan and the high-pressure compressor rotational speeds is released.

4. The bypass ratio control method under the condition of simulating a complete turbofan engine according to claim 1, characterized in that: The same or similar means that the fan pressure ratio or the high-pressure compressor pressure ratio is no more than 10% of the corresponding pressure ratio under the whole machine state.

5. The bypass ratio control method under the condition of simulating a complete turbofan engine according to claim 1, characterized in that: The predetermined rotation speed interval does not exceed 100 rpm.

6. A method for regulating bypass ratio under simulated turbofan engine complete machine conditions, characterized in that: Based on a biaxial compressor tester, the method comprises: Determine the control parameters under the whole machine state, the control parameters include the speed matching relationship between the fan and the high-pressure compressor, the fan blade angle adjustment law, the high-pressure compressor blade angle adjustment law, the fan operating point pressure ratio, and the high-pressure compressor operating point pressure ratio; Determine the control accuracy of the test state control parameters of the biaxial compressor tester; Constructing a control module, which stores the speed matching relationship of the fan and the high-pressure compressor in the whole machine state, the fan blade angle adjustment law and the high-pressure compressor blade angle adjustment law, and is used to make the speeds of the fan and the high-pressure compressor in a linkage mode during the test; Monitor the fan pressure ratio, adjust the outer throttle valve, make the fan pressure ratio the same or similar to that of the whole machine, then adjust the inner throttle valve, monitor the high-pressure compressor pressure ratio at the same time, make the high-pressure compressor pressure ratio the same or similar to that of the whole machine, and then adjust the inner throttle valve and the outer throttle valve at the same time, so that the high-pressure compressor pressure ratio and the fan pressure ratio meet the control accuracy requirements; Keep the state of the biaxial compressor tester stable, collect compressor parameters through the outer exhaust gas collection device and the inner exhaust gas collection device of the biaxial compressor tester, the compressor parameters include fan and high-pressure compressor flow, pressure ratio, efficiency, blade angle and bypass ratio, the stable state is the basic state design point when changing the turbine guide vane area or adjusting the tail nozzle area; According to the fan pressure ratio and high-pressure compressor pressure ratio adjusted according to the turbine guide vane area or tail nozzle area, adjust the internal throttle valve and the external throttle valve at the same time to make the fan pressure ratio and the high-pressure compressor pressure ratio the same as those in the whole machine state, and collect the compressor parameters after the state point stabilizes.

7. The bypass ratio control method under the condition of simulating a complete turbofan engine according to claim 6, characterized in that: Determine the control accuracy of the test state control parameters of the biaxial compressor tester including: The control accuracy of the converted speed of the fan and high-pressure compressor is determined to be 0.2%, the adjustment accuracy of the blade angle of the fan and high-pressure compressor is 0.5°, and the control accuracy of the pressure ratio of the fan and high-pressure compressor is 0.3%.

8. The bypass ratio control method under the condition of simulating a complete turbofan engine as claimed in claim 6, characterized in that: The same or similar means that the fan pressure ratio or the high-pressure compressor pressure ratio is no more than 10% of the corresponding pressure ratio under the whole machine state.

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