Performance test platform for aircraft impeller fuel pump and hydraulic turbine pump

Abstract

The invention relates to the technical field of aviation equipment maintenance, in particular to a performance test platform for an aircraft impeller fuel pump and a hydraulic turbine pump, and aims to solve the problems that in the prior art, after an RLB-33 impeller fuel pump and an RLB-34 hydraulic turbine pump are maintained, performance verification is lack of an integrated and dynamic coupling test environment, and the performance test efficiency is high. The system comprises a test bench system, a power driving system, a pressure flow adjusting system, a measurement control system, a working medium storage and processing system, a gas path control system and a safety protection system. By the adoption of the technical scheme, integrated dynamic coupling performance verification of the RLB-33 impeller fuel pump and the RLB-34 hydraulic turbine pump can be achieved, verification comprehensiveness, accuracy and reliability of the fuel pump after maintenance are remarkably improved, and flight potential safety hazards are effectively reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aviation equipment maintenance, and particularly relates to a performance test platform for a liquid turbine pump of an aircraft impeller fuel pump. BACKGROUND

[0002] In the field of aviation equipment, the fuel supply system is a core link for ensuring the power output and flight safety of an aircraft. The RLB-33 impeller fuel pump and the RLB-34 liquid turbine pump are key core components of the system. The RLB-33 undertakes the functions of fuel delivery and pressure boosting, and the output pressure and flow rate of the RLB-33 directly affect the stability of the fuel supply of an engine. The RLB-34 takes the high-pressure fuel output by the RLB-33 as a power source to realize secondary pressure boosting or flow rate regulation. The RLB-33 and the RLB-34 work together to form a power transmission chain of the fuel system of an aircraft.

[0003] Due to the complex aviation flight environment, the two pumps may have problems such as impeller wear, seal failure, and pressure boosting efficiency reduction after long-term use, and the performance needs to be restored through maintenance. However, the performance verification of the product after maintenance depends on a professional test platform, otherwise the performance of the component may not meet the standards, thereby causing potential flight safety hazards.

[0004] With the extension of the service life of aviation equipment, the maintenance demand for the RLB-33 / 34 series pumps increases year by year. According to the aviation equipment maintenance standard, the fuel pump and the liquid turbine pump after maintenance need to pass three types of core tests before being delivered: a running-in test to simulate low-load operation to eliminate the assembly gap of the component and verify the smoothness of the moving pair, so as to avoid early wear; a performance test to detect key parameters such as inlet and outlet pressure, flow rate, and pressure boosting value under rated and extreme conditions, to ensure that the design requirements are met; and an evaluation test to finally verify the maintenance quality and issue authoritative test data as the core basis for the product to return to the aircraft sequence.

[0005] At present, the detection after traditional maintenance mainly depends on single machine testing or simple tooling, and lacks an integrated test solution for the RLB-33 / 34 series, which has certain limitations in precision, safety, and standardization. SUMMARY

[0006] The application provides a performance test platform for an aircraft impeller fuel pump hydraulic turbine pump, and aims to solve the technical problems of insufficient system performance matching, difficult transient response evaluation and incomplete potential fault mode identification caused by lack of integrated and dynamic coupling test environment in the performance verification process of RLB-33 impeller fuel pump and RLB-34 hydraulic turbine pump after maintenance. The application can accurately simulate the dynamic interaction of the two pumps under real flight conditions by constructing an integrated test system, realize various test modes such as running-in test, performance test, evaluation and detection retest, maintenance delivery acceptance test and the like, reserve performance expansion test interfaces for similar series products, and can be reused as a high-pressure fuel source, so that the performance verification level and flight safety of the fuel pump after maintenance are comprehensively improved.

[0007] To achieve the above-mentioned purpose, the application adopts the following scheme: a performance test platform for an aircraft impeller fuel pump hydraulic turbine pump is provided, comprising: A test bench system is arranged to fix the RLB-33 impeller fuel pump and the RLB-34 hydraulic turbine pump, and provide a connection interface of a fuel circuit and a hydraulic circuit; A power driving system is arranged to provide adjustable mechanical driving force for the RLB-33 impeller fuel pump, and provide high-pressure fuel power output by the RLB-33 impeller fuel pump required for the operation of the RLB-34 hydraulic turbine pump; A pressure and flow regulating system is arranged in the fuel circuit, and is arranged to accurately regulate the outlet pressure of the RLB-33 impeller fuel pump and the outlet flow and pressure increase value of the RLB-34 hydraulic turbine pump; A measurement and control system is arranged to collect various operating parameters in the test process in real time, and perform data processing, storage, display, analysis and automatic control of the test process; A working medium storage and processing system is arranged to store, filter, cool and stabilize aviation fuel and hydraulic oil required for the test; an air path control system is arranged to realize vacuum suction of the fuel tank and exhaust function of the pipeline; And a safety protection system is arranged to monitor the operating state of the test platform, and take linkage protection measures in abnormal conditions.

[0008] Preferably, the test bench system comprises an RLB-33 fuel pump test bench and an RLB-34 hydraulic turbine pump test bench; the RLB-33 fuel pump test bench is provided with a product mounting base for mounting the RLB-33 impeller fuel pump, an oil collecting disc and a waste oil storage tank; the product mounting base is connected with the hydraulic motor of the power driving system through a coupling.

[0009] As preferred, the working oil tank of the RLB-34 hydraulic turbine pump test bench is internally provided with a mounting adapter tool for mounting the RLB-34 hydraulic turbine pump, and the wall of the working oil tank is provided with multiple interfaces for pressure, temperature and liquid level detection, and interfaces for vacuumizing and exhausting; the fuel inlet end of the RLB-34 hydraulic turbine pump is arranged inside the working oil tank, and the fuel outlet end is arranged outside the working oil tank.

[0010] As preferred, the power driving system comprises an RLB-33 driving unit and an RLB-34 power source supply unit; the RLB-33 driving unit comprises a swash plate type axial plunger hydraulic motor and two parallelly arranged electro-hydraulic proportional load-sensitive plunger pumps; the RLB-33 driving unit further comprises an air-oil cooler and a precision oil return filter.

[0011] As preferred, the RLB-34 power source supply unit directly uses the fuel outlet of the RLB-33 impeller fuel pump as the power source input, and sequentially arranges an explosion-proof pneumatic ball valve, a high-pressure precision filter, a flow meter display and a pressure meter display in the pipeline.

[0012] As preferred, the working medium storage and processing system comprises a main fuel tank and a hydraulic driving oil tank, and a fuel processing unit; the main fuel tank is internally provided with a heat exchange coil for adjusting the temperature of fuel, a defoaming device for eliminating fuel foam, and is equipped with high and low liquid level alarm sensors.

[0013] As preferred, the fuel processing unit comprises a fuel filling module, a fuel discharging module, a filtering module, a cooling module and an oil-gas separation module; the fuel filling module comprises a pneumatic diaphragm pump filling trolley; the fuel discharging module comprises a pipeline pump and multiple explosion-proof ball valves; the filtering module comprises an RFA-800-5 type filter for ensuring that the fuel contamination meets the GJB420A-96 standard; the cooling module comprises a stainless steel plate heat exchanger and a refrigeration machine for accurately controlling the fuel temperature in the range of 15℃ to 70℃; the oil-gas separation module comprises an oil-gas processor for ensuring that the oil content of the separated fuel is not greater than 10ppm.

[0014] As preferred, the pressure and flow regulating system comprises an RLB-33 fuel outlet pressure regulating mechanism and an RLB-34 fuel outlet flow and pressure boost value regulating mechanism; the RLB-33 fuel outlet pressure regulating mechanism comprises an electric regulating valve arranged on the outlet pipeline of the RLB-33 impeller fuel pump, and the valve opening degree is PID closed-loop controlled by the feedback signal of the fuel outlet pressure sensor according to the measurement control system; the RLB-34 fuel outlet flow and pressure boost value regulating mechanism comprises a large flow regulating valve and a small flow regulating valve arranged on the outlet pipeline of the RLB-34 hydraulic turbine pump, and the valve opening degree of the large flow regulating valve and the small flow regulating valve is accurately controlled by the electric actuator.

[0015] As preferred, the gas path control system comprises an air compressor, a vacuum pump and a plurality of explosion-proof electromagnetic valves; the air compressor has a rated exhaust volume of not less than 0.5 m3 / min and a rated exhaust pressure of not less than 0.8 MPa; the vacuum pump has a limit vacuum degree of not less than -0.095 MPa and an air extraction rate of not less than 10 L / s, and is used for vacuumizing the working oil tank in the RLB-34 liquid turbine pump test bench.

[0016] As preferred, the safety protection system is further provided with a plurality of distributed emergency stop buttons and integrates a user permission management system.

[0017] Through the above technical scheme, the present application has the following beneficial effects: The performance test platform for the liquid turbine pump of the aircraft impeller fuel pump breaks through the limitation that the traditional single machine test or simple tooling cannot simulate the interaction between pumps, realizes the dynamic coupling test of the RLB-33 impeller fuel pump and the RLB-34 liquid turbine pump, can truly simulate the power transmission chain working condition that the RLB-33 drives the RLB-34 for secondary pressurization as a power source, effectively detects the flow matching, pressure transmission efficiency and transient response characteristics when the two pumps work cooperatively, so as to identify the system-level hidden trouble that is difficult to find in single machine test, and ensures that the components after maintenance meet the power demand in complex flight environment.

[0018] Based on the integrated architecture, the present application has comprehensive test capability in the whole process and in multiple modes, covers the running-in test for eliminating the assembly gap of components, the rated and limit working condition performance test for verifying key parameters, and the final evaluation and detection retest and delivery acceptance test, avoids the flow of components between different devices, significantly shortens the maintenance and detection cycle, and improves the support efficiency of aviation equipment. Meanwhile, cooperating with the high-precision measurement control system, the present application realizes the automatic control of the test process and the real-time acquisition and processing of data, eliminates human recording errors, and automatically generates a standardized test report, providing objective and authoritative data support for the product returning to the machine sequence.

[0019] In terms of ensuring test safety and equipment life, the present application filters, cools and stabilizes the fuel and hydraulic oil through a perfect working medium storage and processing system, ensures that the medium is in the best state to prevent secondary damage to the precision pump body, cooperates with the vacuum suction function of the gas path control system and the multiple safety linkage protection mechanism, effectively eliminates the cavitation risk and sudden failure hidden danger. In addition, the present application also considers the universality and expandability in design, not only reserves the performance expansion interface of similar series products, but also can be directly reused as an independent high-pressure fuel source, greatly improves the comprehensive utilization rate of the equipment, and effectively reduces the construction and maintenance cost of the test facility. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a whole system principle diagram of a performance test platform for a liquid turbine pump of an aircraft impeller fuel pump in an embodiment of the present application.

[0021] Figure 2 is a schematic diagram of a hydraulic and fuel pipeline of a performance test platform for a liquid turbine pump of an aircraft impeller fuel pump in an embodiment of the present application. Figure 3 is a schematic diagram of a structural arrangement of a performance test platform for a liquid turbine pump of an aircraft impeller fuel pump in an embodiment of the present application.

[0022] Figure 4 is a schematic diagram of a hardware architecture of a measurement control system in an embodiment of the present application.

[0023] Fig. 1 is a schematic diagram of a test bench system; Fig. 2 is a schematic diagram of a power driving system; Fig. 3 is a schematic diagram of a pressure flow regulating system; Fig. 4 is a schematic diagram of a measurement control system; Fig. 5 is a schematic diagram of a working medium storage and processing system; Fig. 6 is a schematic diagram of an air path control system; Fig. 7 is a schematic diagram of a safety protection system; Fig. 11 is a RLB-33 fuel pump test bench; Fig. 12 is a RLB-34 liquid turbine pump test bench; Fig. 100 is a RLB-33 impeller fuel pump; Fig. 112 is an oil collecting disc; Fig. 121 is a working oil tank; Fig. 200 is a RLB-34 liquid turbine pump; Fig. 22 is a RLB-34 power source supply unit; Fig. 211 is a hydraulic motor; Fig. 212 is a plunger pump; Fig. 223 is a flow sensor; Fig. 224 is a pressure sensor; Fig. 32 is a RLB-34 fuel outlet flow and pressure increasing value regulating mechanism; Fig. 311 is an electric regulating valve; Fig. 321 is a large flow regulating valve; Fig. 322 is a small flow regulating valve; Fig. 41 is a hardware platform; Fig. 42 is a software platform; Fig. 411 is an industrial control computer; Fig. 412 is a data acquisition card; Fig. 413 is a programmable logic controller; Fig. 414 is an industrial display; Fig. 415 is an uninterruptible power supply; Fig. 51 is a main fuel tank; Fig. 52 is a hydraulic driving oil tank; Fig. 53 is a fuel processing unit; Fig. 511 is a heat exchange coil; Fig. 512 is a defoaming device; Fig. 513 is a liquid level sensor; Fig. 533 is a filtering module; Fig. 534 is a cooling module; Fig. 535 is an oil and gas separation module; Fig. 5341 is a heat exchanger; Fig. 5342 is a refrigeration machine; Fig. 5351 is an oil and gas processor; Fig. 61 is an air compressor; Fig. 62 is a vacuum pump; Fig. 71 is an emergency stop button; Fig. 72 is a transparent protective cover; Fig. 73 is a leakage detection sensor; Fig. 76 is a rotating speed sensor; Fig. 77 is a safety valve; Fig. 79 is a temperature sensor. DETAILED DESCRIPTION

[0024] The specific embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0025] In view of the extreme complexity and harshness of the aviation flight environment, the RLB-33 and RLB-34 series pumps will inevitably encounter a series of performance degradation problems such as wear, corrosion, aging of sealing elements, and decay of boost efficiency during long-term service. To ensure the sustained airworthiness and flight safety of aviation equipment, it is essential to periodically repair, refurbish and restore the performance of these core components. According to the current aviation equipment maintenance standards, any repaired fuel pump and hydraulic turbine pump must undergo a series of rigorous performance verification tests before being put back into use.

[0026] Performance verification tests usually include a running-in test to eliminate assembly gaps between components and verify the smoothness of moving parts by simulating low-load operation, thereby effectively avoiding early wear; a performance test to accurately detect key operating parameters such as inlet and outlet pressures, flow rates, and boost values under rated and even extreme conditions to ensure full compliance with original design requirements; finally, a final and authoritative verification of repair quality is conducted through evaluation and detection retest and factory acceptance test, and test data with legal effect is issued as the core basis for the product to return to the machine sequence.

[0027] Currently, traditional post-repair detection practices rely on single-machine testing or simple tooling, which to some extent meets the verification needs of the basic functionality of individual components.

[0028] However, with the aviation technology putting forward more stringent requirements for system-level performance reliability, and the increasingly close dynamic coupling characteristics between fuel pumps and turbine pumps, the inherent limitations of existing single-machine testing mode are becoming increasingly apparent. The root cause lies in the fact that RLB-33 and RLB-34 are not independent individuals but highly interactive subsystems, with the output characteristics of RLB-33 directly constituting the input conditions of RLB-34, thereby deeply affecting the boost efficiency and regulation accuracy of RLB-34. In the traditional single-machine testing environment, even if RLB-33 and RLB-34 are strictly verified separately, the test conditions are often based on idealized, static or pre-set input parameters.

[0029] For example, when testing RLB-34, its power source is usually provided by an independent, stable high-pressure fuel system, rather than simulating the dynamic and even slightly fluctuating fuel output that RLB-33 may produce under different speeds and loads in real flight. This decoupled testing method, while verifying the performance of individual components under certain conditions, cannot fully reveal or predict the secondary problems, performance decay or unexpected new failure modes that may occur when the two work together as a whole under real flight conditions.

[0030] Specifically, the inherent defects of the separated test are reflected in many aspects: first, it is difficult to accurately simulate the transient response and dynamic interaction of the two pumps under complex variable load conditions. During take-off, landing, climbing, cruising and maneuvering flight, the fuel demand and engine speed will change dramatically, which requires RLB-33 and RLB-34 to quickly and stably adjust their output. Single machine test cannot capture how the small deviation of RLB-33 output parameter is amplified or inhibited by RLB-34 at the system level, nor can it verify the dynamic matching of the entire power transmission chain.

[0031] Secondly, due to the lack of comprehensive evaluation of energy conversion efficiency under actual coupling working condition, the repaired components may perform well in single machine test, but the system level supercharging efficiency or flow regulation accuracy cannot meet the expectation after actual installation, resulting in increased fuel consumption or unstable power output. This performance trade-off effect is hidden and difficult to detect in separate test.

[0032] In addition, single machine test or simple tooling has natural limitations in data acquisition synchronization, accuracy and environmental simulation reality, and it is difficult to establish a complete database with high confidence that can fully reflect the performance indicators of RLB-33 / 34 series pumps in integrated operation. Not only restricts the accurate assessment of component health status, but also hinders the further development of predictive maintenance and fault diagnosis technology.

[0033] Therefore, how to build a professional test platform that can accurately simulate the real dynamic coupling relationship between RLB-33 impeller fuel pump and RLB-34 hydraulic turbine pump, realize integrated comprehensive performance verification, and provide high precision and high reliability test data has become a key challenge and technical problem to be solved for technical personnel in the field.

[0034] The embodiment of the application provides a performance test platform for an aircraft impeller fuel pump and hydraulic turbine pump, which aims to comprehensively improve the technical level of RLB-33 impeller fuel pump and RLB-34 hydraulic turbine pump in the performance verification process after repair. The test platform can accurately simulate the interaction of the two pumps under actual flight conditions by building an integrated and dynamically coupled test environment, realize various verification modes such as running-in test, performance test, evaluation and detection retest, and maintenance delivery acceptance test, and reserve performance expansion test interface for similar series products in the future, and can be reused as a high-pressure fuel source, thereby effectively solving the problems of lack of system level performance matching evaluation, difficulty in transient response evaluation and incomplete identification of potential fault modes in the prior art, and significantly improving the performance verification level and flight safety of the repaired components.

[0035] As Figures 1-4As shown, the embodiment of the present application proposes a performance test platform for an aircraft impeller fuel pump hydrodynamic turbine pump, which comprises: A test bench system 1 is arranged to fix the RLB-33 impeller fuel pump 100 and the RLB-34 hydrodynamic turbine pump 200, and provide a connection interface of the fuel circuit and the hydraulic circuit; A power driving system 2 is arranged to provide adjustable mechanical driving force for the RLB-33 impeller fuel pump 100, and provide the high-pressure fuel power output by the RLB-33 impeller fuel pump 100 for the operation of the RLB-34 hydrodynamic turbine pump 200; A pressure and flow rate regulating system 3 is arranged in the fuel circuit, and is arranged to accurately regulate the outlet pressure of the RLB-33 impeller fuel pump 100 and the outlet flow rate and pressure increase value of the RLB-34 hydrodynamic turbine pump 200; A measurement and control system 4 is arranged to collect various operating parameters in real time during the test process, and perform data processing, storage, display, analysis and automatic control of the test process; A working medium storage and processing system 5 is arranged to store, filter, cool and stabilize the aviation fuel and hydraulic oil required for the test; and an air path control system 6 is arranged to realize the vacuum suction of the fuel tank and the exhaust function of the pipeline; And a safety protection system 7 is arranged to monitor the operating state of the test platform, and take linkage protection measures in abnormal conditions.

[0036] The test bench system 1 is not a single general workbench, but is designed in sub-zones according to the structural differences of the measured objects, and is specifically divided into an RLB-33 fuel pump test bench 11 and an RLB-34 hydrodynamic turbine pump test bench 12. The split type layout not only ensures the independence and convenience of the installation of different pump bodies, but also realizes the unity of the system level through the shock-absorbing foundation at the bottom and the public pipeline corridor.

[0037] On the side of the RLB-33 fuel pump test bench 11, the high-speed and high-vibration characteristics of the pump as a driving source are fully considered, and therefore a product installation base made of thickened steel is arranged, and the base is precisely processed with positioning pin holes and T-shaped grooves for quickly and accurately fixing the RLB-33 impeller fuel pump 100.

[0038] In order to prevent the fuel from leaking and polluting the environment or causing fire hazards during the test process, a stainless steel oil collecting pan 112 is integrally arranged below the installation base, and the bottom of the oil collecting pan is connected to the underground waste oil storage tank through an oil guide pipe to realize the centralized collection and treatment of the leaked medium. The mechanical driving interface of the RLB-33 is connected to the output shaft of the hydraulic motor 211 in the power driving system 2 through a high-precision elastic coupling, and a protective cover with quick release function is arranged outside the coupling to consider safety and maintenance convenience.

[0039] Unlike the mechanical drive mode of RLB-33, RLB-34 hydraulic turbine pump 200 is driven by high-pressure fluid, and has special requirements for the inlet pressure environment. Therefore, the bench body contains a working oil tank 121 with excellent sealing performance, which not only serves as a fluid container, but also as a simulated working environment cabin for RLB-34. Inside the working oil tank 121, a specially customized mounting adapter tool is provided, which can adapt to the complex shell flange of RLB-34 and stably suspend or support it at a specific height inside the oil tank.

[0040] The wall of the working oil tank 121 is made of high-strength alloy steel and can withstand internal vacuum negative pressure. A plurality of standardized quick connectors are circumferentially distributed on the wall, which are respectively used for connecting pressure sensor 224, temperature sensor 79, liquid level sensor 513 and vacuum and exhaust pipelines connected to air path control system 6.

[0041] The fuel inlet end of RLB-34 hydraulic turbine pump 200 is directly placed below the fuel liquid level inside the working oil tank 121 to simulate the oil suction environment at the bottom of the aircraft fuel tank, and the fuel outlet end is extended to the outside of the working oil tank 121 through a wall sealing structure to connect the downstream test pipeline. Not only does it solve the problem of pump body heat dissipation, but more importantly, it can truly simulate the low-pressure environment during high-altitude flight in cooperation with the vacuum system, thereby effectively verifying the cavitation margin and oil suction performance of the pump.

[0042] As shown in Figure 1 and Figure 2 , the power drive system 2 includes an RLB-33 drive unit and an RLB-34 power source supply unit 22. The RLB-33 drive unit is mainly responsible for converting electrical energy into mechanical energy to drive the rotation of RLB-33. In order to realize wide-range and high-precision speed control, this embodiment does not use traditional variable frequency motor direct drive, but selects hydraulic drive scheme.

[0043] Specifically configured: two parallelly arranged electro-hydraulic proportional load-sensitive plunger pumps 212 are used as primary power sources, which can automatically adjust the output flow according to the load pressure change, significantly reducing energy consumption and heat; the hydraulic oil drives the swash plate type axial plunger hydraulic motor 211 to rotate after precise filtration, which has extremely low rotational inertia and excellent low-speed stability, and can simulate the slow vehicle state of RLB-33 during the starting stage of the aero-engine and the full afterburner state during the take-off stage.

[0044] In order to ensure the long-term stable operation of the hydraulic system, a wind-oil cooler and a precise oil return filter are connected in series in the circuit to ensure that the hydraulic oil temperature is maintained in the optimal working interval of 40-60°C, and the cleanliness meets the NAS16386 level standard.

[0045] In the traditional discrete test, RLB-34 is usually driven by an independent external pump station, which leads to the test results unable to reflect the real working condition when it matches with RLB-33. In the embodiment, the power source supply unit 22 of RLB-34 directly uses the fuel outlet of the RLB-33 impeller fuel pump 100 as the power source input, forming a pump-pushing pump cascade test architecture. The high-pressure fuel flowing out from the RLB-33 outlet, through a connecting pipeline simulating the actual pipeline length and flow resistance characteristics of the aircraft, flows through the explosion-proof pneumatic ball valve, high-pressure precision filter, high-frequency response flow metering display and pressure metering display in turn, and finally enters the turbine driving port of RLB-34, so that the output pressure fluctuation and flow pulsation of RLB-33 can be truly transmitted to RLB-34, thereby the potential mismatching problems of the two in terms of resonance frequency and pressure wave transmission can be sharply captured.

[0046] In order to ensure that the physical and chemical properties of the fluid medium remain constant throughout the test cycle, the working medium storage and processing system 5 includes a main fuel tank 51, a hydraulic drive oil tank 52, and a fully functional fuel processing unit 53.

[0047] The main fuel tank 51 is made of 304 stainless steel, and the volume is designed to meet the needs of 5 minutes of circulation under the maximum flow condition, to ensure sufficient heat dissipation and degassing time. The internal structure of the tank is complex, with a labyrinth partition to prolong the fluid path and promote bubble floating; the heat exchange coil 511 at the bottom can be connected to steam or hot water for heating, or to cooling water for cooling. The defoaming device 512 is located at the oil return port and adopts a multi-layer metal screen structure, which can break the large air bubbles generated by the oil jet.

[0048] The fuel processing unit 53 is a bypass circulation system, including a fuel filling module, a fuel discharge module, a filter module 533, a cooling module 534, and an oil-gas separation module 535. Among them, the filter module 533 selects RFA-800-5 type high-precision filter, with filter precision up to 5 microns, ensuring that the fuel contamination strictly meets the GJB420A-96 standard, preventing small particle abrasion of the precise pump body mating surface.

[0049] The cooling module 534 is composed of a stainless steel plate heat exchanger 5341 and an industrial refrigeration machine 5342, which can accurately control the fuel temperature in the wide temperature range of 15℃ to 70℃ through the feedback adjustment of the temperature control instrument, meeting the simulation test needs under different climate conditions.

[0050] The oil-gas processor 5351 in the oil-gas separation module 535 utilizes the principles of centrifugal separation and vacuum coalescence to separate the air and oil vapor mixed in the fuel, ensuring that the gas content of the separated fuel is extremely low, and the oil content is not more than 10ppm, which is crucial for ensuring the accuracy of flow metering and preventing cavitation.

[0051] In the fluid circuit, the pressure flow regulating system 3 is used to accurately regulate the test working condition. For RLB-33, its outlet pressure is a key indicator of pump performance, so the RLB-33 fuel outlet pressure regulating mechanism is set on the outlet pipeline, and the main executive element is a high-response electric regulating valve 311. The valve core of the regulating valve is specially hardened to resist erosion, and its opening degree is not manually adjusted, but is closed-loop controlled by the PID algorithm according to the real-time feedback signal collected by the pressure sensor 224 in the pipeline, and the steady-state control accuracy can reach ±0.05 MPa.

[0052] For RLB-34, the test focuses on its supercharging capacity and flow characteristics, so the RLB-34 fuel outlet flow and supercharging value regulating mechanism 32 is set. Considering the large span of the test flow range, a single valve cannot meet the adjustment resolution, so a large flow regulating valve 321 and a small flow regulating valve 322 are used in parallel. The small flow valve is used for fine adjustment of small pressure difference, and the large flow valve is used for load simulation of the main passage, both of which are driven by electric actuator with position feedback, and can realize automatic flow scanning test with system software.

[0053] The air circuit control system 6 provides necessary auxiliary power and environmental simulation means for the test platform. The system integrates an air compressor 61 and a vacuum pump 62. The selected model of the air compressor 61 has a rated exhaust capacity of not less than 0.5 m³ / min and a rated exhaust pressure of not less than 0.8 MPa. The high-pressure air generated is dried and oil mist separated, and then supplied to pneumatic ball valves, diaphragm pumps and other pneumatic components, to ensure that the actuator operates quickly and powerfully.

[0054] The vacuum pump 62 is a key equipment for RLB-34 test, with an ultimate vacuum degree of not less than -0.095 MPa and a pumping rate of not less than 10 L / s. Before the oil absorption performance test of RLB-34, the vacuum pump 62 is started to perform vacuumizing operation on the working oil tank 121 in the RLB-34 liquid turbine pump test bench 12, and the vacuum degree is adjusted to simulate the process of air pressure reduction in the oil tank during aircraft climbing, so as to verify the oil supply capacity of RLB-34 at different altitudes, which cannot be realized by conventional normal pressure test bench.

[0055] As shown in Figure 4 The hardware architecture of the measurement control system 4 adopts an upper and lower computer structure. The upper computer is a high-performance industrial control computer 411, which runs monitoring software developed based on LabVIEW or C#, provides a human-computer interaction interface, is responsible for test task issuing, data storage, curve drawing and report generation. The core of the lower computer is a programmable logic controller 413, which is responsible for bottom logic operation, safety interlocking and PID loop control.

[0056] The data acquisition card 412, as a bridge connecting the sensors and the computer, has high sampling rate and high resolution, and can collect tens of signals such as rotation speed, torque, pressure, flow, temperature and vibration in real time. In order to ensure the authenticity and synchronicity of the data, the system uses a unified clock source. The software platform 42 is built-in with various standard test programs, including running-in test program, performance test program, durability test program and the like, and the operator only needs to select the corresponding product model and test type, and the system can automatically adjust the motor speed and valve opening to complete the test according to the predetermined curve, greatly reducing the dependence on the experience of the operator.

[0057] In addition, the system is also configured with an industrial display 414 for on-site monitoring, and an uninterruptible power supply 415 to prevent sudden power failure from causing data loss or equipment damage.

[0058] The safety protection system 7 is throughout the corners of the whole platform, and builds multiple protective networks. First, the emergency stop button 71 at the hardware level is distributed in the console, the test bench on both sides and the power station and the like, which are easy to touch, and once an emergency occurs, pressing any button can cut off the main power supply and close all pneumatic cut-off valves.

[0059] Secondly, the physical isolation protection is provided, and the high-speed rotating parts and the high-pressure pipeline area are provided with transparent protective covers 72, which can not only affect the observation but also block the potential mechanical splashing.

[0060] In terms of environmental monitoring, the leakage detection sensor 73 is installed below the oil collection tray and the pipeline joint, and once the fuel accumulation is detected, an alarm is given. The rotation speed sensor 76 is not only used for measurement, but also for overspeed protection; the safety valve 77 is arranged on all pressure-bearing containers and pipelines, and serves as the last physical barrier to prevent overpressure explosion; the temperature sensor 79 monitors the oil temperature in real time to prevent overheating from causing fire. In addition, the introduction of the user permission management system ensures that only authorized and trained personnel can modify the key control parameters, avoiding the risk of misoperation.

[0061] The specific working process of the test platform in the embodiment of the application will be described in detail below, taking a typical RLB-33 and RLB-34 joint maintenance verification test as an example.

[0062] Before the test starts, the operator first performs preparation work. The operator logs in the system through the man-machine interface of the measurement control system 4, checks whether the liquid levels of the main fuel tank 51 and the hydraulic drive oil tank 52 are within the normal range, and if the liquid level is too low, the system will prompt to supplement the liquid through the oil filling module. At the same time, the system automatically performs sensor self-checking and valve zeroing operation, and after confirming that there is no fault code, enters the standby state.

[0063] Then, the operator installs the repaired RLB-33 impeller fuel pump 100 to the RLB-33 fuel pump test bench 11, connects the shaft coupling and fastens the foot bolts; installs the RLB-34 hydraulic turbine pump 200 to the working oil tank 121 of the RLB-34 hydraulic turbine pump test bench 12, connects the inlet and outlet pipelines and sensor interfaces, and closes the sealing cover of the working oil tank 121.

[0064] In the running-in test phase, in order to eliminate the mechanical clearance after the pump body is assembled, the operator selects the running-in mode on the software, at this time the power driving system 2 is started, the RLB-33 driving unit controls the hydraulic motor 211 to drive the RLB-33 to rotate at low speed. At this time, the low-pressure fuel output by the RLB-33 enters the RLB-34 power source supply unit 22 to drive the RLB-34 to rotate slowly. The adjusting valves in the pressure and flow regulating system 3 are in full opening or low damping state, so that the system is in light load cycle. The control system monitors the bearing temperature and vibration value in real time, if the value is stable and there is no abnormal sound within the specified time, it is determined that the running-in is passed, the system automatically increases the speed to enter the next phase until the running-in requirement of the rated speed is reached.

[0065] After the running-in is completed, the performance test phase, i.e. dynamic coupling test, is automatically entered. At this time, the system simulates the aircraft take-off or cruising working condition. The RLB-33 driving unit accelerates the RLB-33 to the rated working speed, and the PID controller starts to intervene to adjust the electric adjusting valve 311 of the RLB-33 fuel outlet pressure regulating mechanism according to the set working condition parameters, so that the RLB-33 outlet pressure is stabilized at the set value. The high-pressure fuel drives the RLB-34 to rotate at high speed as the power source. At the same time, the measurement and control system 4 adjusts the RLB-34 fuel outlet flow and pressure increase value regulating mechanism 32 to change the load characteristics of the RLB-34 by controlling the opening degrees of the large flow adjusting valve 321 and the small flow adjusting valve 322.

[0066] In this process, the data acquisition card 412 synchronously collects the speed, driving torque, outlet pressure and flow of the RLB-33, and the turbine speed, pump outlet pressure and pressure increase value of the RLB-34 at high frequency. The system software automatically calculates the matching efficiency and pressure transmission loss of the two, and draws the P-Q (pressure-flow) characteristic curve. In order to verify the transient response, the system instructs the RLB-33 driving unit to change the speed in steps (simulates the acceleration and deceleration of the engine), and observes the following response speed and pressure overshoot of the RLB-34, so as to identify the dynamic performance defects of the system level.

[0067] If oil absorption performance or high-altitude simulation test is required, the vacuum pump 62 in the gas path control system 6 is started to pump the working oil tank 121 where the RLB-34 is located, so that the internal absolute pressure is reduced to the pressure value corresponding to the altitude. At this time, the above performance test process is repeated, and the pressure fluctuation of the RLB-34 outlet is monitored. If the pressure drops more than the standard value, the cavitation performance is judged to be unqualified.

[0068] After the test is completed, the system enters the shutdown program. First, gradually reduce the RLB-33 rotating speed to idle speed, then start the cooling module 534 to run at full power, and reduce the oil temperature to the safe range. Then, the hydraulic pump station is closed in turn, and the fuel circuit is cut off. The operator uses the oil discharge module in the fuel treatment unit 53 to open the pipeline pump and explosion-proof ball valve, and discharges the residual oil in the RLB-33 and RLB-34 and the pipeline back to the main fuel tank 51 or the waste oil storage tank to prevent fuel from spilling during disassembly. Finally, the test report containing all test data, curves and qualification determination is automatically generated by the measurement and control system 4 and stored in the database for traceability.

[0069] The performance test platform for the liquid turbine pump of the aircraft impeller fuel pump proposed in the embodiment of the application successfully breaks through the limitations of traditional single machine testing through the above structural design and logical control. It not only can be used as a high-precision test table for RLB-33 and RLB-34 independently, but also more importantly realizes the real coupling of the two in physics and fluid power. This integrated test environment enables maintenance personnel to accurately reproduce the complex power transmission process in the air on the ground, greatly improving the fault recognition rate and shortening the maintenance cycle. At the same time, the perfect configuration of the system in medium processing, safety protection and automatic control ensures the efficiency, safety and environmental protection of the test process, and has high engineering application value and popularization prospect. In addition, the platform is designed with sufficient hydraulic and electrical interfaces, which can be easily expanded to test other models of fuel pumps in the same series in the future, or directly used as an independent high-pressure and high-flow fuel source to serve the research and development test of other aviation accessories, showing excellent versatility and scalability.

[0070] The present application is not limited to the specific technical solutions described in the above embodiments. In addition to the above embodiments, the present application can also have other implementation manners. Any modification, equivalent replacement, improvement, etc. made by those skilled in the art within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A performance testing platform for a hydraulic turbine pump used in an aircraft impeller fuel pump, characterized in that, include: The test bench system is equipped with a mounting system for fixing the RLB-33 impeller fuel pump and the RLB-34 hydraulic turbine pump, and provides connection interfaces for the fuel circuit and the hydraulic circuit. The power drive system is used to provide adjustable mechanical driving force for the RLB-33 impeller fuel pump and to provide the RLB-34 hydraulic turbine pump with the high-pressure fuel power output by the RLB-33 impeller fuel pump required for its operation. The pressure and flow regulation system is installed in the fuel circuit to precisely regulate the outlet pressure of the RLB-33 impeller fuel pump and the outlet flow and boost value of the RLB-34 hydraulic turbine pump. The measurement and control system is used to collect various operating parameters during the test in real time, and to process, store, display, analyze, and automate the test process. Working medium storage and processing system, used for storing, filtering, cooling and stabilizing aviation fuel and hydraulic oil required for testing; The gas path control system is used to realize the functions of vacuum suction of the fuel tank and venting of the pipeline; It also includes a safety protection system to monitor the operating status of the test platform and take coordinated protective measures in case of abnormalities.

2. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 1, characterized in that, The test bench system includes the RLB-33 fuel pump test bench and the RLB-34 hydraulic turbine pump test bench. The RLB-33 fuel pump test bench is equipped with a product mounting base, an oil collection tray, and a waste oil storage tank for installing the RLB-33 impeller fuel pump. The product mounting base is connected to the hydraulic motor of the power drive system via a coupling.

3. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 2, characterized in that, The working oil tank of the RLB-34 hydraulic turbine pump test bench is equipped with an installation adapter for installing the RLB-34 hydraulic turbine pump. The wall of the working oil tank is equipped with multiple interfaces for pressure, temperature and liquid level detection, as well as interfaces for vacuuming and venting. The fuel inlet of the RLB-34 hydraulic turbine pump is located inside the working oil tank, and its fuel outlet is located outside the working oil tank.

4. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 1, characterized in that, The power drive system includes an RLB-33 drive unit and an RLB-34 power source supply unit; The RLB-33 drive unit includes a swashplate axial piston hydraulic motor and two parallel electro-hydraulic proportional load-sensitive piston pumps. The RLB-33 drive unit also includes an oil cooler and a precision return oil filter.

5. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 4, characterized in that, The RLB-34 power supply unit directly uses the fuel outlet of the RLB-33 impeller fuel pump as the power source input, and its pipeline is sequentially equipped with an explosion-proof pneumatic ball valve, a high-pressure precision filter, a flow meter display, and a pressure meter display.

6. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 1, characterized in that, The working medium storage and processing system includes a main fuel tank and a hydraulic drive tank, as well as a fuel processing unit; The main fuel tank is equipped with a heat exchange coil for regulating fuel temperature, an anti-foaming device for eliminating fuel foam, and high and low level alarm sensors.

7. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 6, characterized in that, The fuel processing unit includes a refueling module, a discharging module, a filtration module, a cooling module, and an oil-gas separation module; The refueling module includes a pneumatic diaphragm pump refueling trolley; The oil discharge module includes a pipeline pump and multiple explosion-proof ball valves; The filtration module includes an RFA-800-5 type filter to ensure that the fuel contamination level meets the GJB420A-96 standard; The cooling module includes a stainless steel plate heat exchanger and a refrigeration unit, used to precisely control the fuel temperature within the range of 15°C to 70°C. The oil-gas separation module includes an oil-gas processor, which is used to ensure that the oil content of the separated fuel is no more than 10 ppm.

8. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 1, characterized in that, The pressure and flow regulation system includes an RLB-33 fuel outlet pressure regulation mechanism and an RLB-34 fuel outlet flow and boost pressure regulation mechanism. The RLB-33 fuel outlet pressure regulating mechanism includes an electric regulating valve installed on the RLB-33 impeller fuel pump outlet pipeline. The valve opening is controlled by the measurement and control system using PID closed-loop control based on the feedback signal from the fuel outlet pressure sensor. The RLB-34 fuel outlet flow and boost pressure regulating mechanism includes a high-flow regulating valve and a low-flow regulating valve installed on the outlet pipeline of the RLB-34 hydraulic turbine pump. Both the high-flow regulating valve and the low-flow regulating valve achieve precise control of the valve opening through an electric actuator.

9. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 1, characterized in that, The pneumatic control system includes an air compressor, a vacuum pump, and multiple explosion-proof solenoid valves. The rated discharge capacity of the air compressor is not less than 0.5 m³ / min, and the rated discharge pressure is not less than 0.8 MPa; The vacuum pump has an ultimate vacuum of not less than -0.095 MPa and a pumping speed of not less than 10 L / s, and is used to evacuate the working oil tank in the RLB-34 hydraulic turbine pump test bench.

10. The performance test platform for aircraft impeller fuel pump hydraulic turbine pump according to claim 1, characterized in that, The safety protection system is also equipped with multiple distributed emergency stop buttons and integrates a user access control system.

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