A comprehensive test system and method for turbojet engine indicators

Abstract

The invention belongs to the technical field of engine testing, and discloses a comprehensive testing system and method for turbojet engine indicators, including a test bench for installing turbojet engine; an auxiliary mechanism includes a cleaning component and an auxiliary component, the auxiliary component includes a fuel supply module and an oxygen supply module, the fuel supply module and the oxygen supply module are respectively connected to the turbojet engine, and the cleaning component is connected to the fuel supply module; a control mechanism includes an auxiliary device controller, the auxiliary device controller is electrically connected to the test bench, the cleaning component, the fuel supply module and the oxygen supply module, and the auxiliary device controller is electrically connected to a host computer. The invention has a high degree of automation, a small workload of manual operation and interpretation, and can automatically realize the control and collection of turbojet engine parameters, conveniently reduce the workload of manual operation, reduce the error caused by manual operation, improve the efficiency and accuracy of measurement, and is suitable for production testing of large quantities of turbojet engines.

Description

Technical Field

[0001] The invention belongs to the technical field of engine testing, and in particular relates to a comprehensive testing system and method for turbojet engine indicators. Background Art

[0002] As the core component of the aircraft power system, the accuracy and reliability of the performance indicators of the turbojet engine have an important impact on the performance of the entire aircraft. Therefore, testing the comprehensive performance of the turbojet engine is an essential step before the turbojet engine leaves the factory.

[0003] The turbojet engine index comprehensive test system is a set of integrated multi-functional test platform, which can measure the key parameters of turbojet engines in real time and accurately, and provide strong support for engine performance evaluation, fault diagnosis and optimization and improvement through data analysis and processing. However, the existing turbojet engine index comprehensive test system is inefficient, and the test data analysis and processing are mostly manually interpreted by designers, which causes testers to spend a lot of time to find key time nodes from massive test data and analyze the thresholds and change rates of various parameters in the data. This is not only time-consuming and labor-intensive, but may also affect the timeliness and effectiveness of the test. At the same time, due to the existence of a large number of manual operations and complex operations, it is inevitable that errors will occur in a certain link, resulting in misjudgment or missed judgment, which may cause adverse consequences and is not conducive to large-scale engine testing; and due to the inefficiency and error-proneness of manual operations, the accuracy of fault location is also relatively low.

[0004] Therefore, the present application designs a comprehensive testing system and method for turbojet engine indicators to solve the above-mentioned technical problems. Summary of the invention

[0005] In order to solve the above technical problems, the present invention proposes a comprehensive testing system and method for turbojet engine indicators.

[0006] To achieve the above object, the present invention provides a comprehensive test system for turbojet engine indicators, comprising:

[0007] A test bench, on which the turbojet engine to be tested is fixedly mounted;

[0008] The auxiliary mechanism comprises a cleaning component and an auxiliary component, wherein the auxiliary component is in communication with the turbojet engine, and the cleaning component is in communication with the auxiliary component; the auxiliary component comprises a fuel supply module and an oxygen supply module, wherein the fuel supply module and the oxygen supply module are respectively in communication with the turbojet engine, and the cleaning component is in communication with the fuel supply module;

[0009] The control mechanism comprises an auxiliary equipment controller, wherein the auxiliary equipment controller is electrically connected to the test bench, the cleaning component, the fuel supply module and the oxygen supplementation module respectively, and the auxiliary equipment controller is electrically connected to a host computer.

[0010] Preferably, the test bench includes a static frame, a dynamic frame is movably arranged on the static frame, a thrust sensor is arranged between the dynamic frame and the static frame, the thrust sensor is electrically connected to the auxiliary equipment controller, and the turbojet engine is fixedly mounted on the dynamic frame.

[0011] Preferably, the fuel supply module includes an electronic scale electrically connected to the auxiliary equipment controller, and the electronic scale is provided with a tooling fuel system electrically connected to the auxiliary equipment controller, and the tooling fuel system is connected to the fuel supply module of the turbojet engine through a fuel pipeline.

[0012] Preferably, the oxygen supply module includes a tooling oxygen supply cylinder, on which a pressure transmitter electrically connected to the auxiliary equipment controller is provided, and the pressure transmitter is connected to the turbojet engine through an oxygen supply pipeline.

[0013] Preferably, the oxygen supplementation module further includes an oxygen cylinder, and the oxygen cylinder is provided with a first pressure reducer, and the first pressure reducer is connected to the pressure transmitter.

[0014] Preferably, the cleaning assembly includes a nitrogen cylinder, and a second pressure reducer is provided on the nitrogen cylinder, and the second pressure reducer is connected to the fuel pipeline provided between the tooling fuel system and the turbojet engine.

[0015] Preferably, the turbojet engine includes a turbojet core engine arranged on the dynamic frame, the turbojet core engine is electrically connected to a turbojet controller, and the turbojet controller is electrically connected to the auxiliary equipment controller.

[0016] Preferably, the auxiliary device controller is electrically connected to a first regulated power supply and a second regulated power supply, and the first regulated power supply and the second regulated power supply have different voltages.

[0017] A comprehensive test method for turbojet engine indicators comprises the following steps:

[0018] Connect to the comprehensive test system and conduct tests to ensure the stable operation of the system;

[0019] Select a turbojet engine to be tested, fix the turbojet engine on a test bench, and electrically connect the turbojet engine to an auxiliary equipment controller;

[0020] Connecting the fuel supply module and the oxygen supply module to the turbojet engine;

[0021] Test various parameters of the turbojet engine according to design requirements, transmit various parameter data to the auxiliary equipment controller, process and feedback the data, and the host computer displays various parameters and outputs the test report;

[0022] The tested turbojet engine is removed and replaced with a new turbojet engine and tested again.

[0023] Preferably, in the step of testing turbojet engine parameters, the turbojet engine parameters tested include static electrical performance test, power adaptability test, intake assembly bleed residual pressure test, hot test performance test, allowed number of starts test, single continuous working time test and test system calibration.

[0024] Compared with the prior art, the present invention has the following advantages and technical effects: the present invention discloses a comprehensive test system and method for turbojet engine indicators, the turbojet engine to be tested is fixed on a test bench, which is convenient for testing, and the test bench adopts a modular design, which can be fixed and tested for turbojet engines of different models, and the fixation is more convenient and the adaptability is stronger; the auxiliary mechanism is used to adjust the working environment of the turbojet engine, and the auxiliary component is used to supply fuel and supplement oxygen to the turbojet engine to ensure the stable operation of the turbojet engine, and the supplementary oxygen can adjust the oxygen content of the intake air, and the operating state of the turbojet engine at different oxygen contents can be tested; the cleaning component is used to reversely clean the fuel supply module to ensure the smoothness of the pipeline of the fuel supply module and maintain stable operation; at the same time, the purge air of the cleaning component can clear the residual air between the fuel supply module and the turbojet engine after each detection The remaining fuel can avoid affecting the retest; the auxiliary equipment controller of the control mechanism serves as the control core of the comprehensive test system of the present application, which can control the operation of the entire comprehensive test system, set different operating parameters, and send control instructions to the turbojet engine. At the same time, the auxiliary equipment controller can also receive the measured operating parameters of the turbojet engine, and adjust the instructions according to the measured parameters, thereby automatically realizing the parameter measurement of the turbojet engine, without the need for manual adjustment and interpretation, thereby improving the degree of automation, higher test accuracy, and reducing the errors of manual adjustment and interpretation, thereby improving the accuracy of the parameters. The auxiliary equipment controller can also form specific data such as charts and graphs for the obtained parameters and display and output them through the host computer. The host computer can also input data, and then input specific instructions to the auxiliary equipment controller to perform adaptive adjustments according to different turbojet engine models.

[0025] The present invention has a high degree of automation and reduces the workload of manual operation and interpretation. It can automatically realize the control and collection of turbojet engine parameters, conveniently reduces the workload of manual operation, reduces the errors caused by manual operation, improves the efficiency and accuracy of measurement, and is suitable for production testing of large quantities of turbojet engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0027] Figure 1 It is a schematic diagram of a comprehensive test system for turbojet engine indicators applied to the present invention;

[0028] Figure 2 This is a schematic diagram of the test bench structure of the present invention;

[0029] Figure 3 This is a flow chart of the static electrical performance detection of the present invention;

[0030] Figure 4 This is a flow chart of power adaptability detection of the present invention;

[0031] Figure 5 This is a flow chart of the exhaust residual pressure detection of the air intake assembly of the present invention;

[0032] Figure 6 This is a hot test performance test flow chart of the present invention;

[0033] Figure 7 This is a flow chart of the detection of the number of starts allowed by the present invention;

[0034] Figure 8 This is a flow chart of the single continuous working time detection of the present invention;

[0035] In the figure: 1. turbojet engine; 2. test bench; 3. auxiliary equipment controller; 4. upper computer; 5. static frame; 6. dynamic frame; 7. thrust sensor; 8. holding ring; 9. electronic scale; 10. tooling fuel system; 11. fuel pipeline; 12. oil inlet solenoid valve; 13. tooling oxygen supply cylinder; 14. pressure transmitter; 15. oxygen supply pipeline; 16. oxygen supply solenoid valve; 17. oxygen supply solenoid valve; 18. oxygen cylinder; 19. first pressure reducer; 20. nitrogen cylinder; 21. second pressure reducer; 22. cleaning solenoid valve; 23. cleaning pipeline; 24. turbojet core engine; 25. turbojet controller; 26. control cable; 27. first regulated power supply; 28. second regulated power supply. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0038] Reference Figure 1-Figure 8 As shown, this embodiment provides a comprehensive test system for turbojet engine indicators, including:

[0039] A test bench 2, on which the turbojet engine 1 to be tested is fixedly mounted;

[0040] The auxiliary mechanism includes a cleaning component and an auxiliary component, the auxiliary component is connected to the turbojet engine 1, and the cleaning component is connected to the auxiliary component; the auxiliary component includes a fuel supply module and an oxygen supply module, the fuel supply module and the oxygen supply module are respectively connected to the turbojet engine 1, and the cleaning component is connected to the fuel supply module;

[0041] The control mechanism includes an auxiliary device controller 3 , which is electrically connected to the test bench 2 , the cleaning component, the fuel supply module and the oxygen supply module respectively, and the auxiliary device controller 3 is electrically connected to the host computer 4 .

[0042] The present invention discloses a comprehensive test system and method for turbojet engine indicators. The turbojet engine 1 to be tested is fixed on a test bench 2, which is convenient for testing. The test bench 2 adopts a modular design and can be fixed and tested for turbojet engines 1 of different models. The fixation is more convenient and the adaptability is stronger. The auxiliary mechanism is used to adjust the working environment of the turbojet engine 1. The auxiliary component is used to supply fuel and supplement oxygen to the turbojet engine 1 to ensure the stable operation of the turbojet engine 1. The supplementary oxygen can adjust the oxygen content of the intake air, and the running state of the turbojet engine 1 at different oxygen contents can be tested. The cleaning component is used to reversely clean the fuel supply module to ensure the smoothness of the pipeline of the fuel supply module and maintain stable operation. At the same time, the purge air of the cleaning component can clear the residual fuel between the fuel supply module and the turbojet engine 1 after each detection, so as to avoid retesting. The auxiliary device controller 3 of the control mechanism is the control core of the comprehensive test system of the present application, which can control the operation of the entire comprehensive test system, set different operating parameters, and send control instructions to the turbojet engine 1. At the same time, the auxiliary device controller 3 can also receive the measured operating parameters of the turbojet engine 1, and adjust the instructions according to the measured parameters, thereby automatically realizing the parameter measurement of the turbojet engine 1, without manual adjustment and interpretation, improving the degree of automation, higher test accuracy, reducing the error of manual adjustment and interpretation, and improving the accuracy of the parameters. The auxiliary device controller 3 can also form the obtained parameters into specific data such as charts and display and output them through the host computer 4, and the host computer 4 can also input data, thereby inputting specific instructions to the auxiliary device controller 3, and adaptively adjusting according to different turbojet engine 1 models. The present invention has a high degree of automation, a small workload of manual operation and interpretation, and can automatically realize the control and collection of turbojet engine 1 parameters, conveniently reducing the workload of manual operation, reducing the error caused by manual operation, and improving the efficiency and accuracy of measurement, and is suitable for mass production and testing of turbojet engines 1.

[0043] Further optimization scheme, the test bench 2 includes a static frame 5, a dynamic frame 6 is movably arranged on the static frame 5, a thrust sensor 7 is arranged between the dynamic frame 6 and the static frame 5, the thrust sensor 7 is electrically connected to the auxiliary equipment controller 3, and the turbojet engine 1 is fixedly mounted on the dynamic frame 6. The static frame 5 is fixed on a base or other fixing mechanism, the dynamic frame 6 is movably connected to the static frame 5, and the thrust sensor 7 arranged between the dynamic frame 6 and the static frame 5 is used to measure the thrust parameters of the turbojet engine 1. The turbojet engine 1 is fixed on the dynamic frame 6. When it is tested, the thrust of the turbojet engine 1 drives the dynamic frame 6 to deflect, and the thrust sensor 7 measures the force between the dynamic frame 6 and the static frame 5, and then measures the thrust state of the turbojet engine 1, and transmits the obtained thrust data back to the auxiliary equipment controller 3, outputs the thrust data, and at the same time serves as feedback data to adjust the operation of the comprehensive test system.

[0044] Furthermore, after the movable frame 6 is installed, the horizontal inclination angles of the table surface in the X direction and the Y direction are ≤3°.

[0045] Furthermore, a quick-detachable holding ring 8 is provided on the movable frame 6 of the present embodiment, the specifications of the holding ring 8 are compatible with the turbojet engine 1 to be tested, and the holding ring 8 can be conveniently replaced and adjusted according to the model of the turbojet engine 1 to be tested, thereby improving the adaptability of the device.

[0046] Furthermore, the holding ring 8 can reliably hold the turbojet engine 1 by means of quick clamping, so as to facilitate loading and unloading.

[0047] Furthermore, the thrust sensor 7 of this embodiment has a measuring range of 0-200kg, a graduation value of 20g, and an accuracy level of III.

[0048] Further optimizing the scheme, the fuel supply module includes an electronic scale 9 electrically connected to the auxiliary equipment controller 3, and the electronic scale 9 is provided with a tooling fuel system 10 electrically connected to the auxiliary equipment controller 3, and the tooling fuel system 10 is connected to the fuel supply module of the turbojet engine 1 through a fuel pipeline 11. The tooling fuel system 10 is used to store fuel, and is provided with an oil pump for outputting fuel, and provides fuel for the operation of the turbojet engine 1 through the fuel pipeline 11; the tooling fuel system 10 is arranged on the electronic scale 9, and the electronic scale 9 is electrically connected to the auxiliary equipment controller 3, and the fuel consumption rate is monitored by real-time monitoring of the remaining amount of fuel.

[0049] Furthermore, the electronic scale 9 of this embodiment has a measuring range of ≤50kg, a graduation value of ≤5g, an accuracy of 0-25kg, and an error within the measuring range of <15g.

[0050] Furthermore, the fuel line 11 of the present embodiment is provided with an oil inlet solenoid valve 12 electrically connected to the auxiliary equipment controller 3 , so as to conveniently control the on-off of the fuel line 11 .

[0051] To further optimize the solution, the oxygen supply module includes a tooling oxygen supply cylinder 13, on which is provided a pressure transmitter 14 electrically connected to the auxiliary equipment controller 3, and the pressure transmitter 14 is connected to the turbojet engine 1 through an oxygen supply pipeline 15; the oxygen supply module also includes an oxygen cylinder 18, on which is provided a first pressure reducer 19, and the first pressure reducer 19 is connected to the pressure transmitter 14. A first pressure reducer 19 is provided on the oxygen cylinder 18, which is used to control the pressure of the oxygen supplied in the oxygen cylinder 18. When the pressure transmitter 14 detects that the pressure in the tooling oxygen supply cylinder 13 is insufficient, the auxiliary equipment controller 3 controls the oxygen supply solenoid valve 16 to open, so that the oxygen after the pressure adjustment is sent into the tooling oxygen supply cylinder 13. After reaching the set pressure, the pressure transmitter 14 outputs a feedback signal, and controls the oxygen supply solenoid valve 16 to be disconnected through the auxiliary equipment controller 3; when starting, the oxygen supply solenoid valve 17 is opened under the control of the controller of the auxiliary equipment controller 3, and oxygen is supplied to the turbojet engine 1 through the oxygen supply pipeline 15 to test the operating status of the turbojet engine 1 under different oxygen-containing environments.

[0052] Further optimization scheme, the cleaning assembly includes a nitrogen bottle 20, and a second pressure reducer 21 is arranged on the nitrogen bottle 20, and the second pressure reducer 21 is connected to the fuel pipeline 11 arranged between the tooling fuel system 10 and the turbojet engine 1. The nitrogen bottle 20 stores nitrogen for cleaning the fuel pipeline 11, and the second pressure reducer 21 can control the supply pressure of nitrogen. After each test is completed, the auxiliary equipment controller 3 controls the cleaning solenoid valve 22 on the cleaning pipeline 23 to open, and empty the residual fuel in the fuel pipeline 11 to avoid affecting the next test; at the same time, the residual fuel in the turbojet engine 1 can be discharged to avoid leakage caused by disassembly and reduce the impact on the environment.

[0053] Further optimizing the scheme, the turbojet engine 1 includes a turbojet core engine 24 arranged on the moving frame 6, and the turbojet core engine 24 is electrically connected to a turbojet controller 25, and the turbojet controller 25 is electrically connected to the auxiliary equipment controller 3. The turbojet core engine 24 is the operating core of the turbojet engine 1, and a number of sensors are arranged therein, which can monitor the rotation speed, temperature and other parameters of the main shaft; the turbojet controller 25 is the control core of the turbojet engine 1, which can control the operation of the turbojet core engine 24, and is quickly connected to the auxiliary equipment controller 3 through a control cable 26 with a quick-release connector, so as to conveniently receive the monitored operating parameters and send control commands to the turbojet engine 1.

[0054] In a further optimized solution, the auxiliary device controller 3 is electrically connected to a first stabilized power supply 27 and a second stabilized power supply 28, and the first stabilized power supply 27 and the second stabilized power supply 28 have different voltages. The first stabilized power supply 27 and the second stabilized power supply 28 are both connected to an external power supply and output a stable voltage to the entire device, providing power supplies of different voltages for the auxiliary device controller 3 to power the device.

[0055] Furthermore, the voltage of the first voltage-stabilized power supply 27 of this embodiment is 0-20V, and is mainly used to provide energy for the solenoid valve of the test system.

[0056] Furthermore, the voltage of the second regulated power supply 28 of this embodiment is 0-32V, and is mainly used to provide energy for the turbojet core engine 24.

[0057] A comprehensive test method for turbojet engine indicators comprises the following steps:

[0058] Connect the comprehensive test system and conduct tests to ensure the stable operation of the system; assemble the test system according to the design plan, and replenish the materials of the oxygen cylinder 18, nitrogen cylinder 20 and tooling fuel system 10 to facilitate the operation of the entire system;

[0059] Select a turbojet engine 1 to be tested, and fix the turbojet engine 1 on the test bench 2, and electrically connect the turbojet engine 1 to the auxiliary equipment controller 3; connect the fuel supply module and the oxygen supplementation module to the turbojet engine 1; select a suitable holding ring 8 to be installed on the dynamic frame 6 according to the specifications and models of the turbojet engine 1 to be tested, and fix the turbojet engine 1 to be tested on the test bench 2 through the holding ring 8, connect the fuel pipeline 11 and the oxygen supplementation pipeline 15 to the corresponding pipelines of the turbojet engine 1, and then connect the auxiliary equipment controller 3 to the turbojet controller 25 through a quick connector for convenient control;

[0060] According to the design requirements, various parameters of the turbojet engine 1 are tested, and the data of various parameters are transmitted to the auxiliary equipment controller 3 and the data are processed and fed back. The host computer 4 displays various parameters and outputs a test report; according to the test requirements, the parameters of the turbojet engine 1 are tested, wherein:

[0061] See attached Figure 3 , the static electrical performance test process includes:

[0062] Self-test: Send self-test instructions and receive self-test results, indicating abnormal self-test failures;

[0063] Ignition head power detection: output ignition head command, lasting for 15 seconds, read the power of the second DC regulated power supply through the auxiliary equipment controller 3, and the average power in the last 5 seconds is ≥25W, which is considered qualified;

[0064] Starter motor drag speed detection: output 1V and 2V voltage instructions for the starter motor, each lasting 15 seconds; when outputting 1V detection instructions, the average speed of the turbojet core engine 24 in the last 5 seconds ≥ the set value, it is judged to be qualified; when outputting 2V detection instructions, the average speed of the turbojet core engine 24 in the last 5 seconds ≥ the set value, it is judged to be qualified; output test report;

[0065] See attached Figure 4 , after the power adaptability detection process starts, the auxiliary equipment controller 3 is respectively provided with a second DC regulated power supply to output 20V and 32V power supply voltages, completes the automatic self-check of the turbojet core engine 24, and outputs a detection report;

[0066] See attached Figure 5 After the intake assembly deflation residual pressure detection process starts, the auxiliary equipment controller 3 sequentially completes the oxygen filling of the tooling oxygen supply cylinder 13, the oxygen exhaust detection of 6 seconds, the oxygen filling of the tooling oxygen supply cylinder 13, the oxygen exhaust detection of 10 seconds, and outputs the detection report;

[0067] See attached Figure 6 , hot test performance test process, manually input the ambient temperature and air pressure, and set different acceptance subjects such as normal temperature working power supply voltage 26V, low temperature working power supply voltage 20V, high temperature working power supply voltage 32V, etc. After starting, the auxiliary equipment controller 3 can control the first DC regulated power supply and the second DC regulated power supply to output the corresponding power supply voltage according to different acceptance subjects, automatically complete the turbojet core engine 24 oxygen supplementation start, non-oxygen supplementation start, speed adjustment and large vehicle speed test instructions, calculate and display the start time, speed control overshoot, speed control adjustment time, speed fluctuation, peak power, large vehicle thrust, large vehicle fuel consumption rate and other indicators, and output the test report;

[0068] See attached Figure 7 , the start-up number detection process is allowed. After it starts, the turbojet core engine 24 automatically completes the oxygen supplementation start, the subsequent five oxygen-free starts and outputs the detection report;

[0069] See attached Figure 8 , a single continuous working time detection process, after starting, the turbojet core engine 24 automatically completes oxygen supplementation start, runs at the design speed for 42 minutes, cleans the oil circuit and outputs the detection report;

[0070] The tested turbojet engine 1 is removed and replaced with a new turbojet engine 1 for another test; after the test is completed, the turbojet engine 1 is cooled to a safe temperature, the turbojet engine 1 is removed, and the test system is reset to facilitate subsequent testing of the turbojet engine 1.

[0071] Further optimize the scheme, in the step of testing the parameters of the turbojet engine 1, the parameters of the turbojet engine 1 tested include static electrical performance detection, power adaptability detection, intake assembly bleed residual pressure detection, hot test performance detection, allowed number of starts detection, single continuous working time detection and test system calibration. The auxiliary equipment controller 3 and the host computer 4 of this implementation are pre-installed with the turbojet core engine 24 acceptance test software, including the core engine status display and control interface, static electrical performance detection module, power adaptability detection module, intake assembly bleed residual pressure detection module, hot test performance detection module, allowed number of starts detection module, single continuous working time detection module, etc., and test system calibration module; at the same time, it can generate a 100HZ test report in any detection module, and save the original test operation data in the hot test performance detection module, allowed number of starts module, and single continuous working time module.

[0072] Furthermore, the core engine status display and control interface has a status display function, which can display status information such as the turbojet core engine 24 motor speed, turbojet core engine 24 speed, exhaust temperature, pump voltage, pump rear oil pressure, and display the turbojet core engine 24 software version; it has the function of zeroing the electronic scale 9 and thrust; it has the function of selecting the detection module.

[0073] Furthermore, the static electrical performance detection module performs a self-test on the turbojet core engine 24 when only the control power is supplied, displays the self-test results and issues an alarm for abnormal results; then, the starting motor dragging and ignition head power detection are performed on the turbojet core engine 24 when only the pool 1 and pool 2 are supplied, respectively, and the detection results are displayed and an alarm is issued for abnormal results.

[0074] Furthermore, the power adaptability detection module can complete the self-test of the turbojet core engine 24 under the condition of only control power supply, display the self-test results and alarm for abnormal results.

[0075] Furthermore, the air intake assembly deflation residual pressure detection module can realize the oxygenation and deflation functions of the work oxygen supply cylinder 13 by controlling the opening and closing of the oxygen supply solenoid valve 16 and the oxygen supplementation solenoid valve 17; at the same time, it can collect the output signal of the pressure transmitter 14, display the residual pressure of the oxygen supplementation cylinder 18 in real time, display the detection results and alarm for abnormal results.

[0076] Furthermore, the hot test performance detection module can complete 24 hot test tests of the turbojet core engine, calculate indicators such as starting time, speed control adjustment time, speed control overshoot, speed fluctuation, vehicle thrust, vehicle fuel consumption rate, etc., display the detection results and alarm for abnormal results.

[0077] Furthermore, the allowed number of starts detection module can complete the allowed number of starts detection of the turbojet core engine 24, display the detection results and alarm for abnormal results.

[0078] Furthermore, the single continuous working time detection module can complete the single continuous working time detection of the turbojet core engine 24, display the detection results and alarm for abnormal results.

[0079] Furthermore, the test system calibration module has the function of calibrating and calibrating the electronic scale 9 and the thrust sensor 7 .

[0080] Furthermore, the auxiliary equipment controller 3 has a start time calculation function, which calculates the time taken from issuing a start command to the speed reaching the set speed for the first time.

[0081] Furthermore, the auxiliary equipment controller 3 has a speed control adjustment time calculation function. During the acceleration process, the time taken for the turbojet core engine 24 to work stably, from the issuance of the speed command to the time when the speed reaches and stabilizes at ±5% of the target speed for the first time, is calculated; and then during the deceleration process, the time taken for the turbojet core engine 24 to work stably, from the issuance of the speed command to the time when the speed reaches and stabilizes at ±5% of the target speed for the first time, is calculated, accurate to 0.1 second.

[0082] Furthermore, the auxiliary equipment controller 3 has a speed control overshoot calculation function. During the acceleration process, when the turbojet core engine 24 is working stably, from the time the core engine speed command is issued, the speed of the turbojet core engine 24 exceeds the maximum difference of the design speed; during the deceleration process, when the turbojet core engine 24 is working stably, from the time the turbojet core engine 24 speed command is issued, the core engine speed is lower than the maximum difference of the design speed, accurate to 10rpm.

[0083] Furthermore, the auxiliary equipment controller 3 has a speed fluctuation calculation function. When the turbojet core engine 24 is working stably, the maximum deviation of the actual speed from the speed command is recorded; after the actual speed reaches the set speed for the second time, the speed fluctuation value begins to be judged. If the set speed is not met twice, the difference in deviation from the set speed in the last 5 seconds of the stable operation stage is judged as speed fluctuation, accurate to 10rpm.

[0084] Furthermore, the auxiliary equipment controller 3 has a vehicle thrust calculation function. When the turbojet core engine 24 speed command reaches the set condition, the arithmetic mean value of the measured thrust for 60 seconds is calculated as the measured vehicle thrust F 实测大车 (Unit: N), then according to the test workshop environment pressure P 环境 (Unit: kPa), trolley thrust F 大车 (Unit: N) is calculated as follows:

[0085]

[0086] If the trolley thrust is greater than or equal to the corresponding trolley thrust requirement value under different ambient temperature conditions, it is judged to be qualified.

[0087] Furthermore, the auxiliary equipment controller 3 has a function of calculating the fuel consumption rate of the vehicle. When the speed of the turbojet core engine 24 reaches the set condition, the weight of the tooling fuel system 10 at 0s and 60s is recorded, and the weight difference is the fuel consumption W 大车 (Unit: kg), the fuel consumption rate of large vehicles is calculated according to the following conversion relationship.

[0088]

[0089] If the truck fuel consumption rate is less than or equal to the corresponding truck fuel consumption rate requirement value under different ambient temperature conditions, it will be judged as qualified.

[0090] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0091] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A comprehensive test system for turbojet engine indicators, characterized in that: include: A test bench (2), on which the turbojet engine (1) to be tested is fixedly mounted; The auxiliary mechanism comprises a cleaning component and an auxiliary component, the auxiliary component being in communication with the turbojet engine (1), and the cleaning component being in communication with the auxiliary component; the auxiliary component comprises a fuel supply module and an oxygen supply module, the fuel supply module and the oxygen supply module being in communication with the turbojet engine (1) respectively, and the cleaning component being in communication with the fuel supply module; The control mechanism comprises an auxiliary equipment controller (3), wherein the auxiliary equipment controller (3) is electrically connected to the test bench (2), the cleaning component, the fuel supply module and the oxygen supply module respectively, and the auxiliary equipment controller (3) is electrically connected to a host computer (4); The test bench (2) comprises a stationary frame (5), a movable frame (6) is movably arranged on the stationary frame (5), a thrust sensor (7) is arranged between the movable frame (6) and the stationary frame (5), the thrust sensor (7) is electrically connected to the auxiliary equipment controller (3), and the turbojet engine (1) is fixedly mounted on the movable frame (6); The movable frame (6) is provided with a holding ring (8) which can be quickly disassembled. The specification of the holding ring (8) is compatible with the turbojet engine (1) to be tested, and the holding ring (8) can be conveniently replaced and adjusted according to the model of the turbojet engine (1) to be tested. The holding ring (8) reliably holds the turbojet engine (1) by means of a quick clamping connection. The oxygen supply module comprises an oxygen supply cylinder (13), the oxygen supply cylinder (13) being provided with a pressure transmitter (14) electrically connected to the auxiliary equipment controller (3), the pressure transmitter (14) being connected to the turbojet engine (1) via an oxygen supply pipeline (15); The oxygen supplementation module further comprises an oxygen cylinder (18), on which a first pressure reducer (19) is arranged, and the first pressure reducer (19) is connected to the pressure transmitter (14); The process of using the comprehensive test system includes the following steps: Connect to the comprehensive test system and conduct tests to ensure the stable operation of the system; Selecting a turbojet engine (1) to be tested, fixing the turbojet engine (1) on a test bench (2), and electrically connecting the turbojet engine (1) to an auxiliary equipment controller (3); Connecting the fuel supply module and the oxygen supply module to the turbojet engine (1); Testing various parameters of the turbojet engine (1) according to design requirements, transmitting various parameter data to the auxiliary equipment controller (3) and processing and feeding back various data, and the host computer (4) displays various parameters and outputs a test report; The tested turbojet engine (1) is removed and replaced with a new turbojet engine (1) to perform the test again; In the step of testing the parameters of the turbojet engine (1), the parameters of the turbojet engine (1) tested include static electrical performance testing, power adaptability testing, intake assembly bleed residual pressure testing, hot test performance testing, allowed number of starts testing, single continuous working time testing, and test system calibration; The auxiliary equipment controller (3) and the host computer (4) are pre-installed with acceptance test software for the turbojet core engine (24), including a core engine status display and control interface, a static electrical performance detection module, a power adaptability detection module, an intake assembly bleed residual pressure detection module, a hot test performance detection module, an allowed number of starts detection module, a single continuous working time detection module, and a test system calibration module; at the same time, a 100 Hz test report can be generated in any detection module, and original test operation data can be saved in the hot test performance detection module, the allowed number of starts module, and the single continuous working time module.

2. The comprehensive test system for turbojet engine indicators according to claim 1, characterized in that: The fuel supply module comprises an electronic scale (9) electrically connected to the auxiliary equipment controller (3); the electronic scale (9) is provided with a tooling fuel system (10) electrically connected to the auxiliary equipment controller (3); the tooling fuel system (10) is connected to the fuel supply module of the turbojet engine (1) via a fuel pipeline (11).

3. The comprehensive test system for turbojet engine indicators according to claim 2 is characterized in that: The cleaning assembly comprises a nitrogen bottle (20), the nitrogen bottle (20) being provided with a second pressure reducer (21), the second pressure reducer (21) being in communication with the fuel pipeline (11) provided between the tooling fuel system (10) and the turbojet engine (1).

4. The comprehensive test system for turbojet engine indicators according to claim 1 is characterized in that: The turbojet engine (1) comprises a turbojet core engine (24) arranged on the moving frame (6), the turbojet core engine (24) being electrically connected to a turbojet controller (25), and the turbojet controller (25) being electrically connected to the auxiliary equipment controller (3).

5. The comprehensive test system for turbojet engine indicators according to claim 1 is characterized in that: The auxiliary device controller (3) is electrically connected to a first regulated power supply (27) and a second regulated power supply (28), wherein the first regulated power supply (27) and the second regulated power supply (28) have different voltages.

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