Aero-engine electric loading test device and system

Abstract

The invention relates to the field of aero-engine performance detection, in particular to an aero-engine electric loading test device and system.The device comprises a main control computer, a temperature sensor, a wind pressure sensor and a plurality of cooling fans, the temperature sensor and the wind pressure sensor are installed in a resistor cabinet, and the resistor cabinet is arranged in a loading room; a plurality of loading resistors are arranged in the resistor cabinet, the output end of the temperature sensor and the output end of the wind pressure sensor are connected with the input end of the main control computer, and the output end of the main control computer is connected with a start-stop switch of the cooling fan; and the heat dissipation fans are arranged at the top and the bottom of the resistor cabinet and on the wall of the loading room. According to the aero-engine electric loading test device, temperature monitoring of the resistor cabinet is achieved by arranging the main control computer and the temperature sensor, hot air in the resistor cabinet is forcibly exhausted by arranging the heat dissipation fan, and the interlocking control function between the temperature sensor and the heat dissipation fan is achieved through the main control computer.

Description

Technical Field

[0001] The invention relates to the field of aero-engine performance testing, and in particular to an aero-engine electric loading test device and system. Background Art

[0002] During the aircraft engine test, there are strict quantitative assessment requirements for the working state of the AC generator. Under different engine states, the electric loading system connects different combinations of load resistors to the main circuit through PLC control. The motor output power is tested by the AC generator with resistors of different resistance values, so as to assess the impact of engine power distribution on engine performance.

[0003] The load resistor will generate a lot of heat during operation. During the electric loading test, it is necessary to pay close attention to the temperature of the electric loading system. When the temperature is too high, it will cause the on-site electrical components to age faster. Therefore, it is necessary to monitor the operating temperature of the loading system. When the temperature is too high, a heat sink is needed to cool it down.

[0004] At present, the heat dissipation of the electric loading system relies on the room wall-mounted ventilation fan, which has poor heat dissipation effect, and cannot monitor the operation of the fan and the system operating temperature, and cannot meet the temperature control requirements in the aircraft engine alternator loading test. There is a fire hazard when the outdoor temperature is high or the system works for a long time. Summary of the invention

[0005] In view of the problems in the prior art, the present invention provides an aero-engine electric loading test device.

[0006] The present invention is achieved through the following technical solutions:

[0007] An aircraft engine electric loading test device comprises a main control machine, a temperature sensor, a wind pressure sensor and a plurality of heat dissipation fans, wherein the temperature sensor and the wind pressure sensor are installed inside a resistor cabinet, the resistor cabinet is placed in a loading room, a plurality of loading resistors are arranged in the resistor cabinet, the output end of the temperature sensor and the output end of the wind pressure sensor are connected to the input end of the main control machine, and the output end of the main control machine is connected to the start and stop switch of the heat dissipation fan; the heat dissipation fan is arranged at the bottom of the resistor cabinet and on the wall of the loading room.

[0008] Preferably, the resistor cabinet adopts a structure of an open cabinet body and a closed door panel.

[0009] Preferably, the heat dissipation fans are named as bottom fans and external exhaust fans according to their installation positions, the bottom fans are arranged at the bottom of the resistor cabinet, and the external exhaust fans are arranged on the wall of the loading room.

[0010] Preferably, an exhaust duct is provided between the interior of the resistor cabinet and the exterior of the loading room for communication, the inlet of the exhaust duct is connected to the top shell of the resistor cabinet, and the outlet is connected to the wall of the loading room; the external exhaust fan is located at the outlet of the exhaust duct.

[0011] Preferably, a heat-insulating layer is wrapped on the outer wall of the exhaust air duct.

[0012] Preferably, a micro switch is provided on the wind pressure sensor, and the micro switch is driven by the static pressure of the gas caused by the rotation of the fan.

[0013] Preferably, the main control machine adopts a PLC control system to control the start and stop of the loading resistor and the cooling fan.

[0014] Preferably, a visual display screen bidirectionally connected to the PLC system is provided on the main control machine, and a human-machine operation interface is configured on the visual display screen.

[0015] Preferably, the main control machine is provided with an alarm indicator light connected to the output end of the PLC system.

[0016] An aero-engine electric loading test system comprises a plurality of the aero-engine electric loading test devices.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] In an aircraft engine electric loading test device of the present invention, a main control computer and a temperature sensor are provided to realize temperature monitoring of a resistor cabinet, a heat dissipation fan is provided to forcibly discharge hot air inside the resistor cabinet, and an interlocking control function between the temperature sensor and the heat dissipation fan is realized by the main control computer.

[0019] Furthermore, an exhaust duct is installed by opening a hole in the top of the resistor cabinet, and an external exhaust fan is installed at the end of the duct. When the external exhaust fan is running, the hot air in the resistor cabinet is forced to be discharged outdoors.

[0020] Furthermore, a PLC system is set up with a temperature sensor and a cooling fan. When the loading resistor in the resistance cabinet starts to load or when the temperature in the resistance cabinet exceeds the set temperature value (such as 50°C), the PLC system will turn on the start and stop switch of the cooling fan for forced exhaust. When the loading test is completed and the temperature drops below 50°C, the fan will automatically stop running, thereby realizing automatic control of the start and stop of the fan by the PLC and avoiding safety hazards caused by the cooling device not being turned on.

[0021] Furthermore, the wind pressure sensor can push the micro switch through the static pressure of the gas to achieve on-off control of the current. When the fan is running, the wind pressure sensor is activated and closed to send a signal to the PLC module. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1It is a schematic diagram of an aero-engine electric loading test device of the present invention;

[0023] Figure 2 It is a schematic diagram of fan control of an aircraft engine electric loading test system of the present invention;

[0024] Figure 3 The invention relates to a human-machine interface for interlocking control of an aero-engine electric loading test system.

[0025] In the figure, 1. resistance cabinet; 2. temperature sensor; 3. exhaust duct; 4. external exhaust fan; 5. bottom fan; 6. wind pressure sensor; 7. loading resistor. DETAILED DESCRIPTION

[0026] The present invention is further described in detail below in conjunction with specific embodiments, which are intended to explain the present invention rather than to limit it.

[0027] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0028] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. 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.

[0029] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0030] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does 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 cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0031] In addition, if the term "horizontal" appears, it does not mean that the component is required to be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0032] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] The present invention discloses an aero-engine electric loading test device, referring to Figure 1 , including a main control computer, a temperature sensor 2, a wind pressure sensor 6 and multiple cooling fans. The temperature sensor 2 and the wind pressure sensor 6 are installed inside the resistance cabinet 1. The resistance cabinet 1 is placed in the loading room. Multiple loading resistors 7 are arranged in the resistance cabinet 1. Among them, the resistance cabinet 1 adopts an open cabinet body with a closed door panel structure, which is convenient for maintenance and operation. Multiple loading resistors 7 are arranged inside to simulate the electrical loading conditions of the aircraft engine.

[0034] The output end of the temperature sensor 2 and the output end of the wind pressure sensor 6 are connected to the input end of the main control machine, and the output end of the main control machine is connected to the start and stop switch of the cooling fan. The temperature sensor 2 and the wind pressure sensor 6 are installed inside the resistance cabinet 1 to monitor the temperature and gas pressure in the cabinet in real time, providing key data for the control of the cooling fan. The micro switch set on the wind pressure sensor 6 can directly respond to the change of gas static pressure caused by the rotation of the fan, which enhances the response speed of the system.

[0035] The main control machine adopts a PLC control system to start and stop the loading resistor 7 and the cooling fan. The main control machine is provided with a visual display screen that is bidirectionally connected to the PLC system, and a human-machine operation interface is configured on the visual display screen so that the operator can observe the start and stop status of the fan through the human-machine operation interface. The main control machine is provided with an alarm indicator light connected to the output end of the PLC system, which can promptly issue an alarm when an abnormality occurs in the system to ensure the safety and reliability of the test process.

[0036] A micro switch is provided in the wind pressure sensor 6, and the micro switch is driven by the gas static pressure caused by the rotation of the fan. That is, the core component inside the selected wind pressure sensor 6 is a micro switch, and its working principle is that the gas static pressure caused by the rotation of the fan pushes the micro switch to turn on, thereby realizing the on-off control of the circuit. When the equipment is started and ventilation is required, the fan will start to rotate. The rotation of the fan will drive the surrounding air to flow, thereby forming a certain gas static pressure at the fan outlet or a specific detection point; as the fan continues to rotate, the gas static pressure will change; the change in gas static pressure will push the micro switch, and after the micro switch is pushed, its internal contacts will change, thereby changing the state of the circuit. If the static pressure is large enough and continuous, the micro switch will remain on, allowing current to pass; conversely, if the static pressure decreases or disappears, the micro switch will disconnect the circuit and cut off the current.

[0037] The heat dissipation fan is installed at the bottom of the resistor cabinet 1 and on the wall of the loading room. The heat dissipation fans are named as bottom fan 5 and external exhaust fan 4 according to the installation position. The bottom fan 5 and the top fan are installed at the bottom and top of the resistor cabinet 1 respectively, and the external exhaust fan 4 is installed on the wall of the loading room. The bottom fan 5 and the top fan directly act on the resistor cabinet 1 to quickly discharge the internal heat; the external exhaust fan 4 discharges the hot air out of the loading room through the exhaust duct 3 to ensure the temperature of the test environment is stable. The fan model is selected according to the fan installation space and the resistor loading power.

[0038] An exhaust duct 3 is arranged between the inside of the resistor cabinet 1 and the outside of the loading room for communication. The inlet of the exhaust duct 3 is connected to the top shell of the resistor cabinet 1, and the outlet is connected to the wall of the loading room. The external exhaust fan 4 is located at the outlet of the exhaust duct 3. The exhaust duct 3 can effectively guide the hot air to be discharged. The inlet of the exhaust duct 3 is arranged on the top shell of the resistor cabinet 1. The selection of this position is based on the physical principle that hot air naturally rises, so that the high-temperature gas accumulated inside the resistor cabinet 1 can naturally converge and flow to the inlet of the duct. The design of the inlet fully considers the sealing and high temperature resistance performance to ensure that the hot air will not leak out, and at the same time can smoothly enter the duct. The outlet of the exhaust duct 3 is planned and installed on the wall of the loading room. The choice of this position is convenient for the centralized discharge of hot air and avoids the direct heat radiation effect on other equipment in the loading room. Not only is an efficient external exhaust fan 4 installed at the outlet, so that the exhaust volume can be flexibly adjusted according to the actual operation of the resistor cabinet 1 and the change of ambient temperature to achieve the optimal heat dissipation effect. In this embodiment, the exhaust duct 3 is made of metal or metal alloy material, and its two ends are fixed by bolts, screws or rivets.

[0039] The outer wall of the exhaust duct 3 is wrapped with an insulation layer, which is used to reduce the heat dissipation of the hot air in the resistor cabinet 1 in the room, further optimize the heat dissipation system of the resistor cabinet 1, reflect the careful consideration of thermal energy management, and also show the active practice in energy conservation and emission reduction. In the selection of the insulation layer, materials with excellent thermal insulation properties are used, such as high-density mineral wool, rock wool, aerogel felt or polyurethane foam. These materials have the characteristics of light weight, corrosion resistance, fire retardancy, etc., which can effectively block the transfer of heat and isolate the high-temperature air inside the resistor cabinet 1 from the external environment, thereby reducing the heat dissipation of hot air to the indoor space during the flow in the duct and discharge to the loading room. The setting of the insulation layer not only helps to reduce heat loss and improve the overall efficiency of the heat dissipation system, but also can reduce the temperature fluctuation in the loading room, creating a more comfortable working environment for the staff. In addition, from the perspective of energy conservation and emission reduction, reducing unnecessary heat loss is also an important part of achieving green and sustainable development goals.

[0040] The invention discloses an aero-engine electric loading test device which can flexibly form a test system of multiple units, and can be centrally managed by a unified main control computer to realize parallel or rotational testing of multiple groups of tests, thereby greatly improving the test efficiency and resource utilization. It integrates modern control technology, data acquisition and analysis technology and advanced power electronics technology to construct a multi-unit test system with powerful functions and convenient operation, and provides strong support for the research and development, performance verification and troubleshooting of aero-engines.

[0041] The core of the present invention lies in its modular design concept, which allows users to flexibly combine test units of different functional modules according to specific test requirements. Each test unit has independent testing capabilities and necessary interface standards to ensure that various types of electrical loads, mechanical stresses and environmental simulation tests can be carried out separately. At the same time, these units are seamlessly connected through standardized communication protocols, realizing high-speed information exchange and sharing, laying the foundation for comprehensive testing of complex systems. In order to achieve centralized and efficient management of multiple groups of tests, the present invention designs a powerful main control system. The system integrates advanced real-time operating systems, multi-task scheduling algorithms and visual monitoring interfaces, can monitor the operating status of each test unit in real time, accurately control test parameters, and automatically switch or execute different test tasks in parallel according to preset test plans. The main control machine also has powerful data analysis and processing capabilities, and can process, analyze and store the collected test data in real time, providing accurate data support for subsequent performance evaluation and fault diagnosis. The aircraft engine electric loading test device of the present invention can support the parallel or rotation testing of multiple groups of tests. This not only greatly shortens the cycle of a single test, improves the test efficiency, but also significantly improves the utilization rate of test resources. When resources are limited or time is tight, users can maximize the test benefits by reasonably arranging the test sequence and optimizing the test resource allocation.

[0042] The present invention also discloses an aircraft engine electric loading test system, including multiple aircraft engine electric loading test devices. In this embodiment, multiple aircraft engine electric loading test devices use the same PLC control system (such as Figure 2 , 3 As shown in the figure, the temperature sensor 2 installed in the resistor cabinet 1 connects its output voltage signal to the PLC system DI module, and displays the current temperature of the resistor cabinet 1 in real time on the WinCC operation interface, and the alarm flashes when the temperature exceeds the set value. When the program in the PLC control system starts loading, or when the temperature exceeds 50℃, the strong exhaust device is automatically turned on. After the loading test, when the temperature drops below 50℃, the fan will automatically stop running.

[0043] The wind pressure sensor 6 is installed in the resistor cabinet 1, and the switch signal is connected to the PLC system for monitoring. The wind pressure sensor 6 can push the micro switch through the static pressure of the gas to realize the on-off control of the current. When the fan is running, the wind pressure sensor 6 is actuated and closed to send the signal to the PLC module. The on-site operator can monitor the operation of the fan in real time through the human-machine interface. When the micro switch of the wind pressure sensor 6 is closed due to the wind pressure, the current in the circuit can flow to form a closed loop. This signal (usually a current or voltage signal) is then sent to the PLC (programmable logic controller) module. The PLC module is a digital operation electronic system designed for industrial environments. It can receive various input signals (such as sensor signals) and process them according to a preset logic program, and finally output a control signal to drive external devices (such as motors, valves, etc.). After receiving the signal from the wind pressure sensor 6, the PLC will judge and process it according to the preset program logic. For example, the speed of the fan may be adjusted according to the size of the wind pressure, or the alarm system may be triggered to remind the operator to pay attention to abnormal conditions.

[0044] The above description is only a preferred embodiment of the present invention and is not intended to impose any limitation on the technical solution of the present invention. Those skilled in the art should understand that, without departing from the spirit and principles of the present invention, the technical solution can also be subjected to several simple modifications and substitutions, and these modifications and substitutions are also within the scope of protection covered by the claims.

Claims

1. An aircraft engine electric loading test device, It is characterized in that The invention comprises a main control machine, a temperature sensor (2), a wind pressure sensor (6) and a plurality of heat dissipation fans. The temperature sensor (2) and the wind pressure sensor (6) are installed inside a resistance cabinet (1). The resistance cabinet (1) is placed in a loading room. A plurality of loading resistors (7) are arranged inside the resistance cabinet (1). The output end of the temperature sensor (2) and the output end of the wind pressure sensor (6) are connected to the input end of the main control machine. The output end of the main control machine is connected to the start and stop switch of the heat dissipation fan. The heat dissipation fan is arranged at the bottom of the resistance cabinet (1) and on the wall of the loading room.

2. The aircraft engine electric loading test device according to claim 1, It is characterized in that The resistance cabinet (1) adopts a structure in which an open cabinet body is matched with a closed door panel.

3. The aircraft engine electric loading test device according to claim 2, It is characterized in that The heat dissipation fans are named as bottom fans (5) and external exhaust fans (4) according to their installation positions. The bottom fans (5) are arranged at the bottom of the resistor cabinet (1), and the external exhaust fans (4) are arranged on the wall of the loading room.

4. The aircraft engine electric loading test device according to claim 2, It is characterized in that An exhaust duct (3) is provided between the interior of the resistor cabinet (1) and the exterior of the loading room for communication; the inlet of the exhaust duct (3) is connected to the top shell of the resistor cabinet (1), and the outlet is connected to the wall of the loading room; an external exhaust fan (4) is located at the outlet of the exhaust duct (3).

5. The aircraft engine electric loading test device according to claim 4, It is characterized in that A heat-insulating layer is wrapped on the outer wall of the exhaust air duct (3).

6. The aircraft engine electric loading test device according to claim 4, It is characterized in that A micro switch is arranged in the wind pressure sensor (6), and the micro switch is driven by the static pressure of the gas caused by the rotation of the fan.

7. The aircraft engine electric loading test device according to claim 1, It is characterized in that The main control machine adopts a PLC control system to control the start and stop of the loading resistor (7) and the cooling fan.

8. The aircraft engine electric loading test device according to claim 7, It is characterized in that A visual display screen bidirectionally connected to the PLC system is arranged on the main control machine, and a human-machine operation interface is configured on the visual display screen.

9. The aircraft engine electric loading test device according to claim 8, It is characterized in that The main control machine is provided with an alarm indicator light which is connected to the output terminal of the PLC system.

10. An aircraft engine electric loading test system, It is characterized in that The invention comprises a plurality of electrical loading test devices for aircraft engines as described in any one of claims 1 to 9.

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