A ground test system and method for hybrid power of aircraft engines

Abstract

The present invention belongs to the technical field of aircraft engine testing, and particularly relates to a ground test system and method for aircraft engine hybrid power; the system comprises a turbine generator and a power supply module, the turbine generator is connected to a mode selection unit via a DC bus; the mode selection unit is respectively connected to a concentrated load module, a zero load module and a distributed load module via a DC bus; the power supply module is connected to the distributed load module via a DC bus; the mode selection unit is signal-connected to an integrated monitoring system and a vehicle platform measurement and control system; the integrated monitoring system is signal-connected to the distributed load module and the concentrated load module; the vehicle platform measurement and control system is signal-connected to the distributed load module, the power supply module and the turbine generator; the vehicle platform measurement and control system is connected to the integrated monitoring system; the mode selection unit is used to select a test mode; rapid switching of test items is achieved, and no human involvement is required during the entire process, thereby avoiding the risks caused by test switching and improving the efficiency of the test.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine testing, and in particular relates to a ground testing system and method for hybrid power of an aero-engine. Background Art

[0002] Existing hybrid electric systems generally include a prime mover, generator, rectifier, distributed electric propulsion (or resistive load system), battery, DC bus, etc. When the energy measurement unit is a resistive load system, it is considered a turbine generator test system. When the resistive load system is replaced with a distributed electric propulsion system and includes batteries, it is considered a series hybrid electric test system. Hybrid electric test projects generally include turbine generator no-load commissioning tests, turbine generator system load commissioning tests, turbine generator system power compliance tests, series hybrid concentrated load tests, and series hybrid distributed electric propulsion tests.

[0003] Existing testing technologies ignore the holistic and progressive nature of hybrid power testing, often designing the aforementioned scenarios on separate test platforms. Even on the same test platform, due to a lack of consideration for the integrity of the test items, rapid switching between test items is impossible, often requiring manual switching of circuits and test equipment. This not only wastes manpower and test costs, but also presents significant deficiencies in test management and carries significant test risks. High voltages may still be present in the test equipment after the test is stopped, and human involvement in the rapid switching of circuits and equipment poses the risk of injury from high voltage. Summary of the Invention

[0004] In response to the above problems, the present invention proposes a ground test system for hybrid power of aircraft engines, comprising a turbine generator and a power supply module, wherein the turbine generator is connected to a mode selection unit through a DC bus; the mode selection unit is respectively connected to a concentrated load module, a zero load module and a distributed load module through a DC bus; the power supply module is connected to the distributed load module through a DC bus; the mode selection unit is signal-connected to an integrated monitoring system and a vehicle platform measurement and control system; the integrated monitoring system is signal-connected to the distributed load module and the concentrated load module; the vehicle platform measurement and control system is signal-connected to the distributed load module, the power supply module and the turbine generator; the vehicle platform measurement and control system is connected to the integrated monitoring system; the mode selection unit is used to select a test mode.

[0005] Furthermore, a load switch No. 1 is provided on the DC bus between the mode selection unit and the distributed load module; a load switch No. 2 is provided on the DC bus between the mode selection unit and the concentrated load module; a load switch No. 3 is provided on the DC bus between the mode selection unit and the zero load module; and a load switch No. 4 is provided on the DC bus between the power supply module and the distributed load module.

[0006] Furthermore, the test modes include mode 1, mode 2, mode 3 and mode 4.

[0007] Furthermore, the turbine power generation device includes an APU, a permanent magnet synchronous generator and an AC-DC module; the APU is connected to the permanent magnet synchronous generator through a shaft, and the permanent magnet synchronous generator is connected to the AC-DC module; the AC-DC module is connected to the mode selection unit.

[0008] Furthermore, when the mode selection unit selects mode No. 1: the distributed load module and the power supply module are controlled by the integrated monitoring system and the vehicle platform measurement and control system to perform a series hybrid distributed electric propulsion test; the power supply module includes a battery and a bidirectional diode.

[0009] Furthermore, when the mode selection unit selects mode No. 2: the centralized load module is controlled by the integrated monitoring system and the vehicle platform measurement and control system to perform a turbine power generation load test.

[0010] Furthermore, when the mode selection unit selects mode No. 3: the zero-load module is controlled by the integrated monitoring system and the vehicle platform measurement and control system to perform a turbine power generation no-load test.

[0011] Furthermore, when the mode selection unit selects mode No. 4: the centralized load module and the power module are controlled by the integrated monitoring system and the vehicle platform measurement and control system to perform a series hybrid power centralized load test.

[0012] Furthermore, it also includes an analysis system, which collects test parameters.

[0013] Furthermore, the centralized load module adopts an electronic load device.

[0014] The present invention further provides a ground test method for aircraft engine hybrid power, which is implemented based on any of the above-mentioned ground test systems for aircraft engine hybrid power, and includes the following steps:

[0015] According to the requirements, the integrated monitoring system selects the test mode through the mode selection unit, and the test modes include mode 1, mode 2, mode 3 and mode 4;

[0016] When mode 1 is selected, load switches 1 and 4 are turned on, and load switches 2 and 3 are turned off; a series hybrid distributed electric propulsion test is conducted;

[0017] When the No. 2 mode is selected, the No. 2 load switch is turned on, and the No. 1 load switch, the No. 3 load switch and the No. 4 load switch are turned off; the turbine generator load test is carried out;

[0018] When the No. 3 mode is selected, the No. 3 load switch is turned on, and the No. 1, No. 2 and No. 4 load switches are turned off; and a no-load test of the turbine generator is carried out;

[0019] When mode No. 4 is selected, load switches No. 2 and No. 4 are connected, and load switches No. 1 and No. 3 are disconnected; a series hybrid power concentrated load test is performed.

[0020] The present invention provides a ground test system for hybrid power of aircraft engines. The vehicle-based measurement and control system issues instructions to the control mode selection unit of the integrated monitoring system to change the test mode, thereby realizing rapid switching of test items. No human participation is required during the entire process, thus avoiding the risks caused by test switching and improving the efficiency of the test.

[0021] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description, claims and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following is a brief introduction to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 The structure diagram of the test system of the present invention is shown.

[0024] Figure 2 A flow chart in an embodiment of the present invention is shown.

[0025] In the figure, 1. Load switch No. 1; 2. Load switch No. 2; 3. Load switch No. 3; 4. Load switch No. 4; 10. Power supply module; 11. Battery; 12. Bidirectional diode; 21. APU; 22. Permanent magnet synchronous generator; 23. AC-DC module; 30. Mode selection unit; 40. Concentrated load module; 50. Zero load module; 60. Distributed load module; 70. Integrated monitoring system; 80. Vehicle measurement and control system; 601. DC-AC module (601-1, 601-2, 601-3 and 601-4); 602. Drive motor (602-1, 602-2, 602-3 and 602-4); 603. Ducted fan (603-1, 603-2, 603-3 and 603-4); 90. Analysis system. DETAILED DESCRIPTION

[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0027] The present application provides a ground test system for hybrid power of aircraft engines, including a turbine generator and a power supply module 10, wherein the turbine generator is connected to a mode selection unit 30 via a DC bus; the mode selection unit 30 is respectively connected to a concentrated load module 40, a zero load module 50 and a distributed load module 60 via a DC bus; the power supply module 10 is connected to the distributed load module 60 via a DC bus; the mode selection unit 30 is signal-connected to an integrated monitoring system 70 and a vehicle platform measurement and control system 80; the integrated monitoring system 70 is signal-connected to the distributed load module 60 and the concentrated load module 40; the vehicle platform measurement and control system 80 is signal-connected to the distributed load module 60, the power supply module 10 and the turbine generator; the vehicle platform measurement and control system 80 is connected to the integrated monitoring system 70; the mode selection unit is used to select a test mode.

[0028] A load switch No. 1 is provided on the DC bus between the mode selection unit 30 and the distributed load module 60; a load switch No. 2 is provided on the DC bus between the mode selection unit 30 and the concentrated load module 40; a load switch No. 3 is provided on the DC bus between the mode selection unit 30 and the zero load module 50; and a load switch No. 4 is provided on the DC bus between the power supply module 10 and the distributed load module 60.

[0029] In one embodiment of the present invention, an analysis system 90 is further included, and the analysis system 90 collects test parameters. During implementation, based on the integrity and progressive relationship of the hybrid-electric test section, the vehicle-based measurement and control system 80, the integrated monitoring system 70 and the analysis system 90 are used to realize the control, data collection and data analysis of the hybrid-electric test section of the aircraft engine.

[0030] The integrated monitoring system 70 is mainly used for measuring test load parameters and controlling load addition and reduction; the test parameters include APU21 (auxiliary power unit) speed, temperature, output shaft power, DC bus voltage, load power and ducted fan 603 speed and other parameters; and some important parameters are transmitted to the vehicle measurement and control system 80 for storage and display; the vehicle measurement and control system 80 is the control and measurement center of the entire test system, including APU21 control, generator, mode selection instructions of the mode selection unit 30 and system parameter measurement, storage and analysis; the analysis system 90 mainly uses a power analyzer to display parameters such as voltage or current waveform, peak value or frequency.

[0031] The load of the distributed load module 60 is controlled by the integrated monitoring system 70; the vehicle platform measurement and control system 80 controls the mode selection unit 30 to select and connect different modules. After receiving the instructions, the integrated monitoring system 70 selects the mode through the mode selection unit 30 to control the opening and closing of different load switches, thereby carrying out the corresponding test process; multiple tests are concentrated in one test system, which facilitates the rapid switching of test lines and equipment, while improving the test efficiency and ensuring the safety of the test process.

[0032] In one embodiment of the present invention, the mode selection unit 30 has multiple built-in experimental modes: the experimental modes include mode 1, mode 2, mode 3 and mode 4; and they can be switched.

[0033] The entire test process is controlled by the vehicle platform measurement and control system 80, and the vehicle platform measurement and control system 80 issues instructions to the integrated monitoring system 70 to control the mode selection unit 30 to select the corresponding mode; and controls the closing and opening of different load switches to make the corresponding modules work and carry out the corresponding test items; when it is necessary to switch the test items, the vehicle platform measurement and control system 80 issues instructions to the integrated monitoring system 70 to control the mode selection unit 30 to change the test mode, thereby realizing rapid switching of the test items. No human participation is required in the entire process, which avoids the risk of the test and improves the efficiency of the test.

[0034] The mode selection unit 30 includes modes 1, 2, 3 and 4, and one or more modes can be selected for testing according to test requirements. At the same time, the starting order of the modes can also be selected according to requirements.

[0035] For example, you can choose mode 1, mode 3 and mode 4; during the test process, you can conduct the test of mode 1, mode 4 and mode 3 in sequence; you can also conduct the test of mode 4, mode 3 and mode 1 in sequence.

[0036] At the same time, mode 2 and mode 3 can be selected; the test sequence can also be changed according to needs; thus increasing the possibilities of conducting tests and expanding the scope of tests.

[0037] In one embodiment of the present invention, the turbine power generation device includes an APU 21, a permanent magnet synchronous generator 22 and an AC-DC module 23; the APU 21 is connected to the permanent magnet synchronous generator 22 via an axis, and the permanent magnet synchronous generator 22 is connected to the AC-DC module 23; the AC-DC module 23 is connected to the mode selection unit 30.

[0038] During the implementation process, the APU21 (auxiliary power unit) drives the permanent magnet synchronous generator 22 and the AC-DC module 23 through the output shaft; the alternating current generated by the permanent magnet synchronous generator 22 is converted through the AC-DC module 23 for easy storage and use, thereby facilitating participation in various tests.

[0039] In one embodiment of the present invention, when the mode selection unit 30 selects mode No. 1: the distributed load module 60 and the power module 10 are controlled by the integrated monitoring system 70 and the vehicle platform measurement and control system 80 to perform a series hybrid distributed electric propulsion test; the power module 10 includes a battery 11 and a bidirectional diode 12.

[0040] The distributed load module 60 includes multiple groups of modules, each group of modules consists of a DC-AC module 601 (601-1, 601-2, 601-3 and 601-4 in the example figure), a drive motor 602 (602-1, 602-2, 602-3 and 602-4 in the example figure) and a ducted fan 603 (603-1, 603-2, 603-3 and 603-4 in the example figure).

[0041] During the test, the integrated monitoring system 70 sends instructions to the mode selection unit 30, selects mode No. 1, and executes the corresponding logic program, thereby connecting the No. 1 load switch 1 and the No. 4 load switch 4 on the DC bus, and disconnecting the No. 2 load switch 2 and the No. 3 load switch 3; the series hybrid distributed electric propulsion test is carried out through the distributed load module 60 and the power supply module 10.

[0042] The distributed load module 60 includes multiple sets of DC-AC modules 601 , a drive motor 602 and a ducted fan 603 .

[0043] The vehicle measurement and control system 80 controls the load of the distributed load module 60, including the speed of the drive motor 602, the speed of the ducted fan 603 and the power output; the integrated monitoring system 70 controls the addition and subtraction of loads to conduct series hybrid distributed electric propulsion tests under different distributed loads.

[0044] The battery 11 and the bidirectional diode 12 are mainly used for charging and discharging, regulating peaks and valleys, and controlling the charging and discharging process through the vehicle platform measurement and control system 80. By collecting the DC bus voltage, energy is stored when the voltage is higher than the threshold range, and energy is released when the voltage is lower than the threshold range; for example, during the test, the rated voltage of the DC bus is DC500V, and charging is performed when it is lower than 435V, and discharging is performed when it is higher than 534V.

[0045] The output shaft of the APU 21 drives the permanent magnet synchronous generator 22 to work. A torque measuring device is provided on the shaft of the APU 21 to measure the torque of the shaft, which can be used for calculation and analysis of system efficiency.

[0046] In one embodiment of the present invention, when the mode selection unit 30 selects the second mode, the centralized load module 40 is controlled by the integrated monitoring system 70 and the vehicle-mounted measurement and control system 80 to perform a turbine generator load test.

[0047] During the test, instructions are issued through the vehicle measurement and control system 80, and the integrated monitoring system 70 controls the mode selection unit 30 to select mode No. 2 and execute the corresponding logic program, thereby connecting the No. 2 load switch 2 on the DC bus and disconnecting the No. 1 load switch 1, No. 3 load switch 3 and No. 4 load switch 4; the turbine generator load test is carried out through the centralized load module 40; the integrated monitoring system 70 monitors the load power of the centralized load module 40.

[0048] In one embodiment of the present invention, when the mode selection unit 30 selects mode 3, the zero-load module 50 is controlled by the integrated monitoring system 70 and the vehicle-mounted measurement and control system 80 to perform a turbine power generation no-load test.

[0049] During the test, instructions are issued through the vehicle-based measurement and control system 80, and the integrated monitoring system 70 controls the mode selection unit 30 to select mode No. 3 and execute the corresponding logic, thereby connecting the No. 3 load switch 3 on the DC bus and disconnecting the No. 1 load switch 1, No. 2 load switch 2 and No. 4 load switch 4; the turbine generator no-load test is carried out through the zero-load module 50; the turbine generator no-load test is mainly used to debug and check whether the APU21 and the permanent magnet synchronous generator 22 are working normally.

[0050] In one embodiment of the present invention, when the mode selection unit 30 selects mode 4, the centralized load module 40 and the power module 10 are controlled by the integrated monitoring system 70 and the vehicle platform measurement and control system 80 to perform a series hybrid centralized load test.

[0051] During the test, the vehicle measurement and control system 80 sends instructions to the mode selection unit 30, selects mode No. 4, and executes the corresponding logic, thereby connecting the No. 2 load switch 2 and the No. 4 load switch 4 on the DC bus, and disconnecting the No. 1 load switch 1 and the No. 3 load switch 3; a series hybrid power concentrated load test is carried out through the concentrated load module 40 and the power module 10; the integrated monitoring system 70 performs parameter measurement on the power of the concentrated load module 40.

[0052] In one embodiment of the present invention, the centralized load module 40 adopts an electronic load device. The electronic load device has higher measurement accuracy than a resistive load or an electric dynamometer, and operates stably.

[0053] The present application provides a ground test method for hybrid power of aircraft engines, the specific steps of which include: first, selecting one or more of mode 1, mode 2, mode 3 and mode 4 according to needs; and arranging the order of selecting each mode test as needed.

[0054] When mode 1 is selected, load switch 1 and load switch 4 are turned on, and load switch 2 and load switch 3 are turned off. First, the vehicle-mounted measurement and control system 80 sends a command to the integrated monitoring system 70, and the integrated monitoring system 70 selects mode 1. During takeoff, the vehicle-mounted measurement and control system 80 gives a command to control the ducted fans 603 in all the multiple groups of modules in the distributed load module 60 to reach the rated speed. At this time, the APU 21 runs to the rated state, and the power module 10 is in the discharge state. During cruising, the vehicle-mounted measurement and control system 80 gives a command to any one or more groups of DC-AC modules 601 (such as Figure 1 For example, there are four groups of DC-AC modules 601, which can be the first and third groups of DC-AC modules 601. The ducted fans 603 of the corresponding groups are controlled to maintain the rated speed, and the other two groups of ducted fans 603 are stopped, and the power module 10 is in a charging state; during the descent process: the vehicle measurement and control system 80 gives an instruction to stop APU21, keeping the power module 10 in a discharging state, and the ducted fans 603 (603-1 and 603-3) corresponding to the first group of DC-AC modules 601 and the third group of DC-AC modules 601 continue to operate.

[0055] When mode No. 2 is selected, load switch No. 2 2 is turned on, and load switch No. 1 1, load switch No. 3 3 and load switch No. 4 4 are turned off; first, the vehicle platform measurement and control system 80 sends an instruction to the integrated monitoring system 70, and the integrated monitoring system 70 selects mode No. 2; then the vehicle platform measurement and control system 80 controls the start of APU21 to run to the rated speed and stay for 2 minutes; then the permanent magnet synchronous motor is controlled to generate electricity and output electric power through the AC-DC module 23; the integrated monitoring system 70 issues a loading power value command; the electronic load device works and absorbs the corresponding power.

[0056] When mode No. 3 is selected, a no-load test of the turbine generator is carried out, the No. 3 load switch 3 is turned on, and the No. 1 load switch 1, the No. 2 load switch 2 and the No. 4 load switch 4 are turned off; first, an instruction is sent to the integrated monitoring system 70 through the vehicle platform measurement and control system 80, and the integrated monitoring system 70 selects mode No. 3; then the vehicle platform measurement and control system 80 controls the start-up of APU21 to run to the rated speed and stay for 2 minutes; then the permanent magnet synchronous motor is controlled to generate electricity, and the electric power is output through the AC-DC module 23.

[0057] When mode No. 4 is selected, load switch No. 2 2 and load switch No. 4 4 are turned on, and load switch No. 1 1 and load switch No. 3 3 are turned off; first, an instruction is sent to the integrated monitoring system 70 through the vehicle platform measurement and control system 80, and the integrated monitoring system 70 selects mode No. 4; the vehicle platform measurement and control system 80 controls the start of APU21 to run to the rated speed and stay for 2 minutes; then the permanent magnet synchronous motor is controlled to generate electricity and output electric power through the AC-DC module 23; APU21 operates in the cruise state, while the battery 11 is in the charging state, and the electronic load device operates at the cruise power; APU21 operates in the rated state, while the battery 11 is in the discharging state, and the electronic load device operates at the maximum power.

[0058] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A ground test system for aircraft engine hybrid power, characterized in that: The invention comprises a turbine generator and a power supply module (10), wherein the turbine generator is connected to a mode selection unit (30) via a DC bus; the mode selection unit (30) is respectively connected to a concentrated load module (40), a zero load module (50) and a distributed load module (60) via the DC bus; the power supply module (10) is connected to the distributed load module (60) via the DC bus; the mode selection unit (30) is signal-connected to an integrated monitoring system (70) and a vehicle platform measurement and control system (80); the integrated monitoring system (70) is signal-connected to the distributed load module (60) and the concentrated load module (40); the vehicle platform measurement and control system (80) is signal-connected to the distributed load module (60), the power supply module (10) and the turbine generator; the vehicle platform measurement and control system (80) is connected to the integrated monitoring system (70); the mode selection unit (30) is used to select a test mode; The test modes include mode 1, mode 2, mode 3 and mode 4; When the mode selection unit (30) selects mode 1, the distributed load module (60) and the power module (10) are controlled by the integrated monitoring system (70) and the vehicle platform measurement and control system (80) to perform a series hybrid distributed electric propulsion test; the power module (10) includes a battery (11) and a bidirectional diode (12); the distributed load module (60) includes a plurality of modules, each module consisting of a DC-AC module (601), a drive motor (602), and a ducted fan (603); When the mode selection unit (30) selects the second mode: the centralized load module (40) is controlled by the integrated monitoring system (70) and the vehicle platform measurement and control system (80) to perform a turbine power generation load test; When the mode selection unit (30) selects mode 3, the zero-load module (50) is controlled by the integrated monitoring system (70) and the vehicle platform measurement and control system (80) to perform a turbine power generation no-load test; When the mode selection unit (30) selects mode No. 4, the concentrated load module (40) and the power module (10) are controlled by the integrated monitoring system (70) and the vehicle platform measurement and control system (80) to perform a series hybrid power concentrated load test.

2. A ground test system for aircraft engine hybrid power according to claim 1, characterized in that: A first load switch (1) is provided on the DC bus between the mode selection unit (30) and the distributed load module (60); a second load switch (2) is provided on the DC bus between the mode selection unit (30) and the concentrated load module (40); a third load switch (3) is provided on the DC bus between the mode selection unit (30) and the zero load module (50); and a fourth load switch (4) is provided on the DC bus between the power module (10) and the distributed load module (60).

3. A ground test system for aircraft engine hybrid power according to claim 2, characterized in that: The turbine power generation device comprises an APU (21), a permanent magnet synchronous generator (22) and an AC-DC module (23); the APU (21) is connected to the permanent magnet synchronous generator (22) via a shaft, the permanent magnet synchronous generator (22) is connected to the AC-DC module (23); and the AC-DC module (23) is connected to a mode selection unit (30).

4. A ground test system for aircraft engine hybrid power according to claim 1 or 3, characterized in that: Also included is an analysis system (90) for collecting test parameters.

5. The ground test system for aircraft engine hybrid power according to claim 1, characterized in that: The centralized load module (40) adopts an electronic load device.

6. A ground test method for hybrid power of aircraft engines, characterized in that: A ground test system for hybrid power of an aircraft engine according to any one of claims 2-3 is implemented, comprising the following steps: according to requirements, the integrated monitoring system (70) selects a test mode through a mode selection unit, the test modes including mode 1, mode 2, mode 3 and mode 4; When the No. 1 mode is selected, the No. 1 load switch (1) and the No. 4 load switch (4) are turned on, and the No. 2 load switch (2) and the No. 3 load switch (3) are turned off to conduct a series hybrid distributed electric propulsion test; When the second mode is selected, the second load switch (2) is turned on, the first load switch (1), the third load switch (3) and the fourth load switch (4) are turned off, and the turbine generator load test is carried out; When the No. 3 mode is selected, the No. 3 load switch (3) is turned on, and the No. 1 load switch (1), the No. 2 load switch (2) and the No. 4 load switch (4) are turned off to conduct a turbine generator no-load test; When the No. 4 mode is selected, the No. 2 load switch (2) and the No. 4 load switch (4) are turned on, and the No. 1 load switch (1) and the No. 3 load switch (3) are turned off to conduct a series hybrid power concentrated load test.

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