Simulation electric load system for airborne test of aero-engine

Abstract

The invention belongs to the field of aircraft flight tests, and relates to a simulation electric load system for an aircraft engine airborne test. Comprising an air inlet, an air compressor, a motor, a plurality of one-way valves, a plurality of pipelines, an adjustable flow port, a resistance wire, an exhaust port, a display controller and a matched cable, the air inlet is communicated with the exhaust port through a first branch, the first branch comprises the pipelines and the one-way valves, the air inlet is communicated with the exhaust port through a second branch, and the second branch comprises the air compressor, the motor and the one-way valves. An inlet of the air compressor is communicated with the air inlet, an outlet of the air compressor is communicated with the interior of the exhaust port through a pipeline, a one-way valve is arranged on the pipeline where the air compressor is communicated with the interior of the exhaust port, an adjustable throttling port is formed in the pipeline inside the exhaust port, and a resistance wire is arranged in the pipeline inside the exhaust port. The output end of the motor is connected with a driving shaft of the air compressor, and the display controller is connected with the control end of the motor through a matched cable and used for controlling the motor.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft flight tests and relates to a simulated electric load system for aircraft engine airborne tests, which can realize the extraction and consumption of aircraft engine electric energy in flight tests, simulate the electric energy load of the aircraft in different working conditions, and is used for aircraft engine performance assessment. Background Art

[0002] In aircraft engine flight tests, an electric load system is usually required to extract and consume power from the aircraft engine's supporting generator, so as to load and test the generator. At present, the electric load system used in aircraft engine flight tests usually uses the principle of resistance heating for power consumption, converts electrical energy into the internal energy of the resistance wire, and uses air or water as a heat dissipation medium. According to its final cooling form, it is divided into air-cooled type, evaporative type, etc. However, the current electric load system is limited by the heat dissipation area, medium capacity, etc., and the maximum power that can be loaded is usually only about 100 to 200 kW, which cannot meet the test verification requirements of new engine high-power generators. Summary of the invention

[0003] Purpose of the invention: The present invention proposes a simulated electric load system for onboard testing of aircraft engines. The system can be installed on an aircraft engine aerial test bench, and converts the electric energy generated by the generator of the aircraft engine into the thermal energy, pressure energy, and mechanical energy of the air by using a combination of principles such as an electric compressor and air-cooled resistance wire, and realizes electric energy consumption through heat dissipation and discharge of air, simulating the electric energy load of the aircraft engine, thereby providing relevant test capabilities of the aircraft engine. Compared with the traditional electric load system for onboard testing of aircraft engines, the system of the present invention converts and consumes electric energy through a combination based on an electric compressor, which can break through the limitations of the traditional system in terms of heat dissipation area, medium capacity, etc., and provide greater electric energy consumption capacity with a smaller volume.

[0004] Technical solution:

[0005] A simulated electric load system for aircraft engine airborne testing includes: an air inlet 1, a compressor 2, an electric motor 3, a plurality of one-way valves 4, a plurality of pipelines 5, an adjustable flow port 6, a resistance wire 7, an exhaust port 8, a display controller 9, and a matching cable 10, wherein:

[0006] The air inlet 1 is connected to the exhaust port 8 through a first branch, the first branch includes a pipeline and a one-way valve 4, the air inlet 1 is connected to the exhaust port 8 through a second branch, the second branch includes a compressor 2, a motor 3, and a one-way valve 4, wherein the inlet of the compressor 2 is connected to the air inlet 1, the outlet of the compressor 2 is connected to the inside of the exhaust port 8 through a pipeline, the pipeline connecting the compressor 2 and the inside of the exhaust port 8 is provided with a one-way valve 4, the internal pipeline of the exhaust port 8 is provided with an adjustable flow port 6, the internal pipeline of the exhaust port 8 is provided with a resistance wire 7, the output end of the motor 3 is connected to the driving shaft of the compressor 2, the display controller 9 is connected to the control end of the motor 3 through a matching cable 10, and is used to control the motor 3.

[0007] Furthermore, the driving motor and the display controller 9 are electrically connected to the adjustable flow port 6 via a matching cable 10 , so as to control the opening of the adjustable flow port 6 .

[0008] Furthermore, the air inlet 1 is the source of the electric load energy conversion medium, and the outside air enters the system pipeline through the air inlet 1.

[0009] Furthermore, the compressor 2 is a main component for converting electric energy. The compressor 2 is driven by an electric motor to compress the air entering from the air inlet 1 to increase its pressure and temperature.

[0010] Furthermore, the electric motor 3 drives the compressor 2 and realizes energy consumption and conversion by consuming electrical energy and converting it into mechanical energy for the rotation of the compressor 2.

[0011] Furthermore, the one-way valve 4 is a core component for controlling the air flow direction in the system pipeline 5. When multiple compressors are connected in parallel, the on-off of the one-way valve 4 is automatically controlled by pressure to ensure the correct flow of air in the system.

[0012] Furthermore, the pipe 5 is a channel for the air medium to flow, and can also withstand changes in the temperature and pressure of the air medium during the operation of the system.

[0013] Furthermore, the adjustable flow port 6 provides a reasonable outlet pressure for the compressor 2 by throttling the air medium, ensuring that it is in a normal working state; at the same time, the throttle port 6 also plays a role in energy conversion. The high-temperature and high-pressure air reduces its pressure when passing through the throttle port, and at the same time, the temperature increases due to the friction with the wall surface, thereby converting the pressure energy into thermal energy, mechanical energy and residual kinetic energy of the air; the throttle port 6 changes its working characteristics through electronic control to adjust the working state of the system. The mechanical structure of the throttle port 6 is located in the exhaust port 8, and the throttle port structure is cooled by the cold air in the outer pipe.

[0014] Furthermore, the resistance wire 7 is an auxiliary component for converting electric energy. Through the Joule heating effect, the electric energy is converted into the heat energy of the resistance wire 7. The resistance wire 7 dissipates heat using air as the medium, and the resistance wire 7 is supplemented to achieve accurate control of the load power of the engine 3.

[0015] Furthermore, the exhaust port 8 is the outlet of the air medium in the system. The air with a certain kinetic energy and a temperature increased after upstream energy conversion is discharged into the atmosphere through the exhaust port; the display controller 9 is a device for user interaction and system operation control. The controller completes the conversion, distribution, and control of the working status of each device of the electric energy drawn from the aircraft engine generator, and provides a visual interface for the user to obtain and control the system working status; the matching cable 10 is used to transmit the electric energy generated by the aircraft engine generator and the control signals of each device.

[0016] Beneficial effects:

[0017] The system of the present invention utilizes a device mainly based on an electric compressor, compresses air as a working medium, processes and discharges it, realizes the conversion and consumption of electric energy, and thus simulates the electric energy load of an aircraft engine. The system of the present invention is used for airborne testing of aircraft engines, and can perform controllable conversion and consumption of high-power electric energy generated by a generator according to the needs of airborne testing. The system has a simple structure and a large adjustment range of working performance. It is no longer limited by the heat dissipation area, medium capacity, etc., and can obtain a stronger aircraft electric load simulation capability than traditional methods with a smaller volume. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A schematic diagram of a simulated electric load system for aircraft engine airborne testing according to the present invention;

[0019] Among them: 1. Air inlet 2. Compressor 3. Motor 4. Check valve 5. Pipeline 6. Adjustable flow port 7. Resistance wire 8. Exhaust port 9. Display controller 10. Matching cables. DETAILED DESCRIPTION

[0020] In practical applications, the traditional electric load system mainly converts the electrical energy generated by the generator of the aircraft engine into thermal energy through the Joule heating effect, and uses water (evaporative type) and air (air-cooled type) as heat dissipation media for continuous heat dissipation, thereby simulating the electrical load during the use of the aircraft engine. In the present invention, air is used as the medium to consume the electrical energy generated by the aircraft engine under test, and an electric compressor is used to compress the medium. The energy is further converted into kinetic energy and thermal energy of the air through a throttling device and discharged. This can increase the air discharge temperature and speed, reduce the system volume, and improve the medium utilization efficiency. At present, in the airborne tests of various aircraft engines, there are no mature application cases of simulated electric load systems using electric compressors as core energy conversion devices.

[0021] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution 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. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0022] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.

[0023] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0024] Figure 1 The figure is a schematic diagram of a simulated electric load system for aircraft engine airborne testing according to an example of the present invention.

[0025] like Figure 1 As shown, a simulated electric load system for aircraft engine airborne testing includes: an air inlet 1, a compressor 2, an electric motor 3, a one-way valve 4, a pipeline 5, an adjustable flow port 6, a resistance wire 7, an exhaust port 8, a display controller 9, and a matching cable 10.

[0026] The air inlet 1 is connected to the exhaust port 8 through a first branch, the first branch includes a pipeline and a one-way valve 4, the air inlet 1 is connected to the exhaust port 8 through a second branch, the second branch includes a compressor 2, a motor 3, and a one-way valve 4, wherein the inlet of the compressor 2 is connected to the air inlet 1, the outlet of the compressor 2 is connected to the inside of the exhaust port 8 through a pipeline, the pipeline connecting the compressor 2 and the inside of the exhaust port 8 is provided with a one-way valve 4, the internal pipeline of the exhaust port 8 is provided with an adjustable flow port 6, the internal pipeline of the exhaust port 8 is provided with a resistance wire 7, the output end of the motor 3 is connected to the driving shaft of the compressor 2, the display controller 9 is connected to the control end of the motor 3 through a matching cable 10, and is used to control the motor 3.

[0027] There can be multiple second branches.

[0028] The air inlet 1 is installed on the aircraft engine airborne test platform, i.e., the outer surface of the aircraft, facing the aircraft heading, and the air enters the system pipe 5 through the ramming effect during the flight of the aircraft. In some embodiments, the side of the aircraft may also be opened, so that the system can enter the pipe 5 through the suction effect of the compressor 2 and the ejection effect at the exhaust port 8 when the system is parked on the ground and when the aircraft is in flight;

[0029] The inlet of the compressor 2 is connected to the air inlet 1 through a pipeline 5. The compressor 2 is driven by the motor 3 to compress the air entering from the air inlet 1 to increase its pressure and temperature. In some embodiments, by connecting multiple compressors 2 and motors 3 in parallel, the power of the electric energy load that can be simulated by the system can be increased.

[0030] The motor 3 directly drives the compressor 2. Meanwhile, the operation of the motor 3 is controlled by the display controller 9. The motor can be a permanent magnet motor or an induction motor. The power and working characteristics of the motor match those of the compressor 2.

[0031] The one-way valve 4 is installed on the outlet pipeline of the compressor 2. The one-way valve ensures the normal working logic of the system. In particular, when multiple compressors are connected in parallel, the one-way valve ensures that a certain compressor will not affect the normal operation of other compressors, and ensures that the medium in the system flows in the correct direction.

[0032] The pipe 5 is a circulation pipe for the air medium between the functional accessories in the system. The pipe can use different diameters and materials in different parts according to the functional requirements. In this embodiment, the pipe 5 is double-layered when flowing through the adjustable flow port, with hot air flowing in the inner layer and cold air flowing in the outer layer. In some embodiments, the pipe direction and topological structure of the pipe 5 need to be adjusted according to the system design and installation conditions.

[0033] The adjustable orifice 6 is electrically driven to change the local flow cross-sectional area to adjust its throttling characteristics. The adjustable orifice 6 will generate temperature rise during use, and it is necessary to use materials and components with good thermal conductivity and heat resistance. In this embodiment, the mechanical structure of the throttle is partially located in the double-layer pipe 5, and the throttle structure is cooled by the cold air in the outer pipe. In some embodiments, in order to improve the heat dissipation efficiency of the throttle structure, the adjustable orifice structure wrapped in the outer cold air pipe can be provided with heat dissipation fins.

[0034] The resistance wire 7 is installed in the pipe 5, and relatively low power is accurately loaded through the Joule heating effect. After loading, the heated resistance wire is cooled by the throttled high-speed airflow. The resistance wire 7 is insulated from the pipe 5. The resistance wire 7 is made of a high-resistance alloy material with high rigidity. In some embodiments, the resistance wire 7 can also be arranged in the outer cold air flow pipe to achieve a better heat dissipation effect by increasing the temperature difference of heat dissipation. In this case, a relatively larger outer air flow is required;

[0035] The exhaust port 8 is the outlet of the air medium in the system. During implementation, a reasonable exhaust port position should be selected according to the characteristics of the aircraft platform to prevent hot air flow from affecting the normal flight of the aircraft and the normal operation of other systems on the aircraft. In this embodiment, the exhaust port 8 is double-layered, the inner layer is high-temperature and high-speed exhaust, and the outer layer is low-temperature and low-speed exhaust. The high-temperature and high-speed exhaust of the inner layer has a certain induced effect on the outer layer exhaust, and can increase the flow rate by increasing the pressure difference at the end of the outer layer pipeline.

[0036] The display controller 9 can realize the conversion and distribution of electric energy and the control of each device in the system, and also provide a visual interface for the user. The user can read the working status of the system and input control instructions through the display controller interface; in some embodiments, the display controller can be split into multiple devices and devices, for example, according to the functions of electric energy conversion, electric energy distribution, display, control, etc., to realize distributed installation on the aircraft platform.

[0037] The supporting cable 9 is used to transmit the electric energy generated by the generator of the aircraft engine and the control signals of various devices.

[0038] In summary, the core of the present invention is to use an electric compressor to compress the air medium, and convert the energy into kinetic energy and heat energy of the air through a throttling device and discharge it. Through this process, the electric energy generated by the aircraft engine generator is consumed, and the electric load of airborne equipment and the like can be simulated for aircraft engine airborne testing. Compared with the traditional air-cooled electric load system with air as the medium, by increasing the air discharge temperature and speed, the medium utilization efficiency is improved, and the simulation of high-power electric load is achieved under the same volume.

Claims

1. A simulated electric load system for aircraft engine airborne testing, characterized in that: include: An air inlet (1), an air compressor (2), an electric motor (3), a plurality of one-way valves (4), a plurality of pipelines (5), an adjustable flow port (6), a resistance wire (7), an exhaust port (8), a display controller (9), and matching cables (10), wherein: The air inlet (1) is connected to the air outlet (8) through a first branch, the first branch includes a pipeline and a one-way valve (4), the air inlet (1) is connected to the air outlet (8) through a second branch, the second branch includes a compressor (2), an electric motor (3), and a one-way valve (4), wherein the inlet of the compressor (2) is connected to the air inlet (1), the outlet of the compressor (2) is connected to the inside of the air outlet (8) through a pipeline, the one-way valve (4) is arranged on the pipeline connecting the compressor (2) and the inside of the air outlet (8), an adjustable flow port (6) is arranged on the pipeline inside the air outlet (8), a resistance wire (7) is arranged in the pipeline inside the air outlet (8), the output end of the electric motor (3) is connected to the drive shaft of the air compressor (2), and the display controller (9) is connected to the control end of the electric motor (3) through a matching cable (10) for controlling the electric motor (3).

2. The simulated electric load system for aircraft engine airborne testing according to claim 1, characterized in that: The driving motor and the display controller (9) are electrically connected to the adjustable flow port (6) via a matching cable (10) and are used to control the opening of the adjustable flow port (6).

3. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The air inlet (1) is the source of the electric load energy conversion medium, and the outside air enters the system pipeline through the air inlet (1).

4. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The compressor (2) is a main component for converting electric energy. The compressor (2) is driven by an electric motor to compress the air entering from the air inlet (1) to increase its pressure and temperature.

5. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The electric motor (3) drives the compressor (2) and realizes energy consumption and conversion by consuming electrical energy and converting it into mechanical energy for the compressor (2) to rotate.

6. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The one-way valve (4) is a core component for controlling the air flow direction in the system pipeline (5). When multiple compressors are connected in parallel, the one-way valve (4) is automatically controlled by pressure to ensure the correct flow of air in the system.

7. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The pipe (5) is a channel for the air medium to flow, and can also withstand changes in the temperature and pressure of the air medium during the operation of the system.

8. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The adjustable flow port (6) provides a reasonable outlet pressure for the compressor (2) by throttling the air medium, thereby ensuring that the compressor (2) is in a normal working state. At the same time, the throttling port (6) also plays a role in energy conversion. When the high-temperature and high-pressure air passes through the throttling port, the pressure is reduced and the temperature is increased due to the friction with the wall surface, thereby converting the pressure energy into heat energy, mechanical energy and the residual kinetic energy of the air. The throttling port (6) changes its working characteristics through electronic control to adjust the working state of the system. The mechanical structure of the throttling port (6) is located in the exhaust port (8), and the throttling port structure is cooled by the cold air in the outer pipe.

9. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The resistance wire (7) is an auxiliary component for converting electric energy. Through the Joule heating effect, the electric energy is converted into the heat energy of the resistance wire (7). The resistance wire (7) dissipates heat using air as a medium. The resistance wire (7) is supplemented to achieve accurate control of the load power of the engine 3.

10. The simulated electric load system for aircraft engine onboard testing according to claim 1, characterized in that: The exhaust port (8) is the outlet of the air medium in the system. The air with a certain kinetic energy and a higher temperature after upstream energy conversion is discharged into the atmosphere through the exhaust port. The display controller (9) is a device used for user interaction and system operation control. The controller completes the conversion, distribution and control of the working state of each device of the electric energy drawn from the aircraft engine generator, and provides a visual interface for the user to obtain and control the system working state. The matching cable (10) is used to transmit the electric energy generated by the generator of the aircraft engine and the control signals of various devices.

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