Test bed for aviation hybrid power turbine power generation system

Abstract

The invention discloses a test bed for an aviation hybrid power turbine power generation system. The test bed comprises a rack system, an emergency load system, a load absorption system, a test system, an electrical control system, a lubricating oil system, a fuel oil system and an exhaust system. According to the invention, the problems of the existing eddy current system during the test are well solved, the test risk is effectively reduced, the test reliability is improved, and the method can be used for the complete machine test of the aviation hybrid power eddy current system; according to the invention, the special protection setting of the engine controller is utilized, the brake and the emergency load system avoid the galloping risk caused by load loss during the test of the high-rotating-speed and high-power eddy current system from the three aspects of fuel control, mechanical braking and emergency load switching, and multiple safety protection measures guarantee each other and act at the same time; requirements of lubricating cooling of the generator, cooling of the generator controller and the like during an eddy current system test are met by means of the independently arranged lubricating oil system, and correct and safe operation of the test bed is guaranteed.

Description

Technical Field

[0001] The present application relates to the technical field of equipment efficiency management, and in particular, to a hybrid power turbine power generation system test bench for aviation. Background Art

[0002] Compared with traditional aircraft engine tests, the test of hybrid turbine power generation system for aviation (abbreviated as turboelectric system) needs to consider the lubrication and cooling of high power density generators, the cooling of generator controllers (rectifiers), the load consumption of high voltage and high current, and the safety issues that may cause the engine to run away due to instantaneous load loss, etc. If necessary, the on-site assembly of turboelectric system needs to be considered. Existing engine test benches and turboelectric system test benches, such as the common turboelectric system test benches, are mainly used for generator sets or ship power. Their volume, weight, power-to-weight ratio, and working characteristics are quite different from those of hybrid turboelectric systems for aviation. The design and application of the corresponding test benches are also very different. They are not suitable for the test of hybrid turboelectric systems for aviation, and the risk of running away in turboelectric system tests cannot be completely avoided. In addition, the protection logic of traditional aircraft engine controllers generally sets threshold protection for specific parameters, such as controlling the engine to stop when the speed exceeds a certain limit value, while the load parameters are mostly indirect values ​​for the engine controller (calculated after calibration) and are generally not connected to the protection logic. In the test of the turbo-electric system, if the load is lost due to generator failure, the existing protection setting that relies solely on engine speed over-limit may cause the fuel to be cut off in time and lead to runaway. Summary of the invention

[0003] The present application provides a hybrid power turbine generator system test bench for aviation, so as to solve the technical problems that the prior art is not suitable for the test of hybrid power turbo-electric systems for aviation and cannot completely avoid the risk of flying cars in the test of turbo-electric systems.

[0004] This application is implemented through the following scheme: A hybrid power turbine power generation system test bench for aviation, comprising: A test bench system for supporting the operation of a turbo-electric system, wherein the turbo-electric system includes a turbine engine, a generator driven by the turbine engine, an engine controller for controlling the operation of the turbine engine, and a generator controller for converting alternating current into direct current; The emergency load system is connected to the vortex-electric system and the generator controller through cables, and is used to switch the normal load circuit to the emergency load circuit within milliseconds when the vortex-electric system loses load instantly; The load absorption system is composed of multiple DC resistive dry-type load cabinets, which are connected to the generator controller circuit and are used for normal loading and absorbing the output electric power of the vortex electric system; The test system measures and collects the operating parameters of the vortex electric system through the test cable, and exchanges real-time data with the engine controller, generator controller, and electrical control system through Ethernet. The operating status, real-time data, and alarm status of each subsystem of the test bench are centrally and remotely monitored on the display terminal of the test system; The electrical control system receives instructions through the operating system, uses PLC as the central processor, adopts a distributed I / O architecture, realizes the engine control instruction input and output and data acquisition functions through DI, DO, AI, AO, and communication module components, and uses the real-time Ethernet of the PROFINET protocol to exchange data with the generator controller, emergency load system, load absorption system, lubricating oil system, and fuel system, thereby realizing the control of the vortex-electric system and test bench equipment; while giving the load absorption system loading power, it sends a signal to the engine controller to form a linkage between the vortex-electric system and the load absorption system, and has an emergency stop function; The lubricating oil system exchanges data with the electrical control system through Ethernet, monitors key parameters such as flow and pressure in real time, and implements remote control to provide the vortex electric system with lubricating oil that meets the requirements; The fuel system exchanges data with the electrical control system through Ethernet, monitors key parameters such as flow and pressure in real time, and implements remote control, provides the vortex electric system with fuel that meets the requirements and has an emergency stop function. In emergency conditions, the fuel supply can be quickly cut off within milliseconds; The exhaust system is installed at the exhaust rear end of the vortex electric system to guide the exhaust gas generated by the vortex electric system and guide the cold air flow to prevent the gas from flowing back.

[0005] Furthermore, the engine controller is specifically used for: Receive the load signal and the engine output shaft speed signal. When the load signal is lost instantaneously or the falling slope is too large, and the power turbine output shaft speed is greater than the set value, the emergency stop protection of the turbine engine is triggered.

[0006] Furthermore, the test bench system has margins in both axial and radial directions to compensate for the thermal expansion generated during the eddy-electric system test.

[0007] Furthermore, the turbine engine and generator of the turbulent electric system adopt a split structure or an integrated structure. When the integrated structure is adopted, the output end of the turbine engine is directly connected to the generator; when the split structure is adopted, a brake is installed between the turbine engine and the generator. When the turbulent electric system loses load in a large state, the transmission shaft speed is directly reduced by the brake, thereby reserving time for the safety measures of the test to take effect.

[0008] Furthermore, the emergency load system includes an emergency load and a switch connected to the emergency load and the generator controller circuit respectively. When a fault occurs in the generator controller, the load absorption system or between the two, causing the vortex electric system to lose load instantly, the switch switches from the load absorption system to the emergency load within milliseconds.

[0009] Furthermore, the emergency load is located on the AC circuit and adopts an air-cooled AC load, an air-cooled DC load with a rectifier, a water-cooled AC load, a water-cooled DC load with a rectifier, an electric dynamometer, an eddy current dynamometer or a grid-connected load.

[0010] Further, the emergency load is consistent with the load of the load absorbing system; or, The emergency load is provided with a predetermined margin compared to the load size of the load absorbing system.

[0011] Furthermore, the switch includes an IGPT switching normally open switch and an IGPT switching normally closed switch, and the IGPT switching normally open switch and the IGPT switching normally closed switch are respectively connected to the emergency load and the generator controller to form an interlocking relationship.

[0012] Furthermore, the fuel system is equipped with a fire damper on the fuel supply pipeline and an external emergency stop oil valve on the oil supply pipeline of the turbine engine. Its emergency stop signal is connected to the electrical control system through a circuit, and under emergency conditions, the fuel supply can be quickly cut off within milliseconds.

[0013] Furthermore, the exhaust system is movable in the axial direction to accommodate turbo-electric systems of different sizes.

[0014] Compared with the prior art, this application has the following beneficial effects: The present application provides a hybrid power turbine power generation system test bench for aviation, which includes a test bench system, an emergency load system, a load absorption system, a test system, an electrical control system, an oil system, a fuel system, and an exhaust system. Starting from the overall design, the present application properly solves the problems faced by the turbo-electric system during the test through the joint adjustment and control of multiple process systems of the test bench, effectively reduces the test risk, and improves the test reliability. It can be used for the whole machine test of the hybrid power turbine power generation system for aviation, and provides equipment support for the development of hybrid power for aviation; the load of the present application is essentially a distributed load cabinet running in parallel, which can be changed by changing the number of load cabinets. Change the load size to adapt to turbo-electric system tests of different powers; the present application utilizes the special protection settings of the engine controller, the brake, and the emergency load system to avoid the risk of runaway caused by load loss during high-speed, high-power turbo-electric system tests from three aspects: fuel control, mechanical braking, and emergency load switching. Various safety protection measures protect each other and work at the same time; the present application relies on an independently set lubricating oil system to solve the needs of lubrication and cooling of the generator and cooling of the generator controller during turbo-electric system tests, ensuring the correct and safe operation of the test bench; the present application uses a test system and an electrical control system to monitor and control the status of all equipment on the test bench, including the test pieces, in real time, with a high degree of automation.

[0015] In addition to the above-described purposes, features and advantages, the present application also has other purposes, features and advantages. The present application will be further described in detail with reference to the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings: Figure 1 This is a schematic diagram of the components of the test bench of the hybrid power turbine power generation system for aviation according to the preferred embodiment of the present application; Figure 2 It is a schematic diagram of the test bench test principle of the hybrid power turbine power generation system for aviation according to the preferred embodiment of the present application; Figure 3 It is a schematic diagram of the components of the test bench of the hybrid turbine power generation system for aviation according to another preferred embodiment of the present application. DETAILED DESCRIPTION

[0017] The embodiments of the present application are described in detail below in conjunction with the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0018] like Figure 1As shown, the preferred embodiment of the present application provides an aviation hybrid turbine power generation system test bench, including a test bench system, an emergency load system, a load absorption system, a test system, an electrical control system, a lubricating oil system, a fuel system, and an exhaust system, wherein: The test bench system is used to support the operation of the vortex electric system, which includes a turbine engine, a generator driven by the turbine engine, an engine controller for controlling the operation of the turbine engine, and a generator controller for converting AC power into DC power. The turbine engine and generator of the vortex electric system adopt a split structure, and a brake is installed between the turbine engine and the generator. In the early stage of development, especially considering the instantaneous loss of load caused by generator failure in extreme cases, it is necessary to consider adding a last mechanical braking safety protection measure for the vortex electric system. Therefore, in this embodiment, when conducting a split vortex electric system test, a brake is installed between the engine and the generator. When the vortex electric system loses load in a large state, the brake works accordingly at the same time, directly physically reducing the speed of the drive shaft, and buying time for the emergency response of the test personnel or other protection settings. For vortex electric systems within the brake speed and power margin, the brake can even be relied on to achieve a complete braking effect. Because of the requirements for response time and applicable power, this type of brake often uses a magnetic powder brake; The emergency load system is connected to the vortex-electric system and the generator controller respectively through cables, and is used to switch the normal load circuit to the emergency load circuit within milliseconds when the vortex-electric system loses load instantly; The load absorption system is composed of a plurality of DC resistive dry-type load cabinets, which are connected to the generator controller circuit and are used for normal loading and absorption of the output electric power of the vortex-electric system. The load absorption system is used for normal loading and absorption of the output electric power of the vortex-electric system. The load absorption system is composed of a plurality of DC resistive dry-type load cabinets. The load absorption system has complete protection functions, anti-interference capabilities, and high insulation strength. The load absorption system needs to work for a long time and is installed outdoors in an environment with ventilation and heat dissipation conditions.

[0019] The test system measures and collects the operating parameters of the vortex electric system through the test cable, and exchanges real-time data with the engine controller, generator controller, and electrical control system through Ethernet. The operating status, real-time data, and alarm status of each subsystem of the test bench are centrally and remotely monitored on the display terminal of the test system. The electrical control system receives instructions through the operating system, uses PLC as the central processor, adopts a distributed I / O architecture, realizes engine control instruction input and output and data acquisition functions through DI, DO, AI, AO, and communication module components, and uses the real-time Ethernet of the PROFINET protocol to exchange data with the generator controller, emergency load system, load absorption system, lubricating oil system, and fuel system, thereby realizing the control of the vortex-electric system and the test bench equipment; while the load absorption system is given loading power, a signal is sent to the engine controller to form a linkage between the vortex-electric system and the load absorption system, and has an emergency stop function; The lubricating oil system and the electrical control system exchange data via Ethernet, monitor key parameters such as flow rate and pressure in real time, and implement remote control to provide the vortex electric system with lubricating oil that meets the requirements; The fuel system and the electrical control system exchange data via Ethernet, monitor key parameters such as flow and pressure in real time, and realize remote control to provide the turboelectric system with fuel that meets the requirements. The fuel system has an emergency stop function, a fire damper is installed on the fuel supply pipeline, and an external emergency stop valve is installed on the fuel supply pipeline of the engine body. Its emergency stop signal is connected to the electrical control system through a hard line. Under emergency conditions, the fuel supply can be quickly cut off within milliseconds, which is faster than the engine body stop valve controlled by the engine controller. The exhaust system is installed at the exhaust rear end of the vortex electric system, and is used to guide the exhaust gas generated by the vortex electric system and guide the cold air flow to prevent the gas from flowing back.

[0020] The present embodiment provides a hybrid power turbine power generation system test bench for aviation, which includes a test bench system, an emergency load system, a load absorption system, a test system, an electrical control system, a lubricating oil system, a fuel system, and an exhaust system. During the test, the test bench system supports the operation of the turbo-electric system. The generator of the turbo-electric system converts the mechanical energy of the turbine engine into electrical energy, outputs it in the form of alternating current and passes through the emergency load system. It is then rectified and converted into direct current by a generator controller, and then absorbed and consumed by the load absorption system, thereby realizing the conversion of mechanical energy-electrical energy-thermal energy.

[0021] The aviation hybrid power turbine power generation system test bench of this embodiment starts from the overall design and properly solves the technical problems faced by the turbo-electric system during the test through the joint adjustment and joint control of multiple process systems of the test bench, effectively reduces the test risk, and improves the test reliability. It can be used for the whole machine test of the aviation hybrid power turbine electric system, and provides equipment support for the development of aviation hybrid power; the aviation hybrid power turbine power generation system test bench of this embodiment adapts to the turbo-electric system test of different powers by changing the capacity of the load absorption system; the aviation hybrid power turbine power generation system test bench of this embodiment utilizes the special protection settings of the engine controller, brakes, emergency load The load system avoids the risk of running away caused by load loss during the test of high-speed and high-power turbo-electric systems from three aspects: fuel control, mechanical braking, and emergency load switching. Various safety protection measures protect each other and work at the same time. The aviation hybrid turbine power generation system test bench of this embodiment relies on an independently set lubricating oil system to solve the lubrication and cooling of the generator and the cooling of the generator controller during the turbo-electric system test, thereby ensuring the correct and safe operation of the test bench. The aviation hybrid turbine power generation system test bench of this embodiment monitors and controls the status of all equipment on the test bench, including the test pieces, in real time through the test system and electrical control system, with a high degree of automation.

[0022] Specifically, in a preferred embodiment of the present application, the engine controller is specifically used for: Receive the load signal and the engine output shaft speed signal. When the load signal is lost instantaneously or the falling slope is too large, and the power turbine output shaft speed is greater than the set value, the emergency stop protection of the turbine engine is triggered.

[0023] In this embodiment, compared with the limit value control protection of traditional aircraft engine tests, the engine controller needs to be specially set to avoid the risk of runaway during eddy current system tests. Figure 2 As shown, the engine controller receives the load signal and the engine output shaft speed signal. When the load signal is lost instantly or the falling slope is too large, and the power turbine output shaft speed is greater than the set value (non-traditional high speed limit threshold), the engine body parking protection can be triggered. Among them, the load signal comes directly from the load absorption system and other equipment, which responds faster and more accurately than the load signal collected and calculated by the engine controller itself.

[0024] Preferably, the test bench system has margins in both axial and radial directions to compensate for the thermal expansion generated during the eddy-electric system test, thereby preventing internal stress caused by heat during the test from affecting the stability and reliability of the test bench.

[0025] Preferably, the emergency load system includes an emergency load and a switch connected to the emergency load and the generator controller circuit respectively. When a fault occurs in the generator controller, the load absorption system, or between the two, causing the vortex electric system to lose load instantly, the switch switches from the load absorption system to the emergency load within milliseconds. During the test, if the vortex electric system loses load instantly due to a fault in the generator controller, the load absorption system, or between the two, the emergency load system can apply the emergency load within milliseconds, effectively reducing the risk of runaway when testing high-speed, high-power vortex electric systems. The principle is that when the electrical control system determines that the fault condition is met, the switch switches the normal load circuit to the emergency load circuit; because the emergency load system is in an AC circuit, the emergency load usually selects an AC load.

[0026] Specifically, the emergency load is located on the AC circuit and adopts an air-cooled AC load, an air-cooled DC load with a rectifier, a water-cooled AC load, a water-cooled DC load with a rectifier, an electric dynamometer, an eddy current dynamometer or a grid-connected load.

[0027] Specifically, the emergency load is consistent with the load of the load absorption system, so as to avoid fluctuations during load switching and ensure that the rotation speed of the turbine blades remains consistent with that before the load switching after the load switching when the load is dropped.

[0028] Alternatively, a predetermined margin is set between the emergency load and the load size of the load absorbing system to ensure a certain design redundancy and improve the safety of the system.

[0029] Preferably, the switch includes an IGPT switching normally open switch and an IGPT switching normally closed switch, and the IGPT switching normally open switch and the IGPT switching normally closed switch are respectively connected to the emergency load and the generator controller to form an interlocking relationship.

[0030] IGBT is a power device with its own tube voltage drop. When the current is too large, a lot of heat will be generated. Therefore, the IGBT module needs to be cooled by an aluminum heat sink. The IGBT module is fixed on the aluminum heat sink. In order to effectively diffuse the heat and increase the contact reliability, thermal grease is applied on the contact surface between the IGBT module and the heat sink, and then the fan is used for air cooling. Each input and output is led out to the input and output port through a cable. Because there are many IGBTs and the current is relatively large, the main circuit and the auxiliary circuit are each divided into two parts, each of which is switched by a three-phase switch. In this way, each part consists of 6 IGBTs and 1 heat sink. A total of 24 IGBTs are fixed on 4 heat sinks.

[0031] The switch of this embodiment adopts IGPT as the switching switch, which has a simple structure and is easy to control, thereby ensuring that the action time of the switch reaches the nanosecond level when performing load switching to avoid test accidents such as turbine blades breaking and flying out. Moreover, since the IGPT switching normally open switch and the IGPT switching normally closed switch are respectively connected to the emergency load and the generator controller and form an interlocking relationship, erroneous switching of the load absorption system and the emergency load system is avoided, thereby ensuring the reliability and safety of load switching.

[0032] Preferably, the switch includes a normally open high-power solid-state relay and a normally closed high-power solid-state relay, and the normally open high-power solid-state relay and the normally closed high-power solid-state relay are respectively connected to the emergency protection load system and the rectifier to form an interlocking relationship.

[0033] The switch of this embodiment uses a high-power solid-state relay as a switch, which has the advantages of high reliability, long life, high sensitivity, low control power, good electromagnetic compatibility, fast conversion, low electromagnetic interference, etc. This ensures that the action time of the switch reaches the nanosecond level when performing load switching, so as to avoid the test accident of the turbine blade breaking and flying out. Moreover, since the normally open high-power solid-state relay and the normally closed high-power solid-state relay are respectively connected to the emergency protection load system and the rectifier and form an interlocking relationship, the load absorption system and the emergency load system are also avoided from switching by mistake, ensuring the reliability and safety of load switching.

[0034] Preferably, the fuel system has an emergency stop function, which includes a fire damper installed on the fuel supply pipeline, an external emergency stop valve on the fuel supply pipeline of the turbine engine, and an emergency stop signal connected to the electrical control system through a circuit. Under emergency conditions, the fuel supply is quickly cut off within milliseconds, which is faster than the stop valve of the turbine engine. The fuel system and the electrical control system exchange data through Ethernet, monitor key parameters such as flow and pressure in real time, and realize remote control.

[0035] Preferably, the exhaust system is movable in the axial direction to accommodate vortex electric systems of different sizes.

[0036] like Figure 2As shown, in the above embodiment, during the test process, the special protection settings of the engine controller, the brake, and the emergency load system are utilized to avoid the risk of running away due to load loss during the test of the high-speed, high-power turbo-electric system from three aspects: fuel control, mechanical braking, and load switching. Various safety protection measures protect each other and work at the same time; at the same time, an independent lubricating oil system is used to solve the problems of lubrication and cooling of the generator and cooling of the generator control; the test bench system can be quickly modified in a modular manner to adapt to the installation and support problems of the integrated or split-structure turbo-electric system; at the same time, the test system and the electrical control system are used to monitor and control all equipment on the test bench, including the status of the test piece, in real time.

[0037] like Figure 3 As shown, different from the above-mentioned embodiment, the turbine engine and generator of the turbo-electric system of this embodiment adopt an integrated structure, and the output end of the turbine engine is directly connected to the generator, with a compact structure, thereby meeting the test needs of the integrated turbo-electric system.

[0038] The above-mentioned embodiment of a hybrid power turbine generator system test bench for aviation can be applied to the test of split or integrated turbo-electric system after modular transformation. The split turbo-electric system is a transition in the development process of the integrated turbo-electric system. Its advantage is that it can be tested and verified at a lower cost and in a shorter time. However, its disadvantage is that the high power density generator technology is not mature enough, and it is very easy to cause a runaway accident caused by a generator body failure.

[0039] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0040] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. A hybrid power turbine power generation system test bench for aviation, characterized in that: include: A test bench system for supporting the operation of a turbo-electric system, wherein the turbo-electric system includes a turbine engine, a generator driven by the turbine engine, an engine controller for controlling the operation of the turbine engine, and a generator controller for converting alternating current into direct current; The emergency load system is connected to the vortex-electric system and the generator controller through cables, and is used to switch the normal load circuit to the emergency load circuit within milliseconds when the vortex-electric system loses load instantly; The load absorption system is composed of multiple DC resistive dry-type load cabinets, which are connected to the generator controller circuit and are used for normal loading and absorbing the output electric power of the vortex electric system; The test system measures and collects the operating parameters of the vortex electric system through the test cable, and exchanges real-time data with the engine controller, generator controller, and electrical control system through Ethernet. The operating status, real-time data, and alarm status of each subsystem of the test bench are centrally and remotely monitored on the display terminal of the test system; The electrical control system receives instructions through the operating system, uses PLC as the central processor, adopts a distributed I / O architecture, realizes the engine control instruction input and output and data acquisition functions through DI, DO, AI, AO, and communication module components, and uses the real-time Ethernet of the PROFINET protocol to exchange data with the generator controller, emergency load system, load absorption system, lubricating oil system, and fuel system, thereby realizing the control of the vortex-electric system and test bench equipment; while giving the load absorption system loading power, it sends a signal to the engine controller to form a linkage between the vortex-electric system and the load absorption system; at the same time, it exchanges data with the test system; in an emergency, when the vortex-electric system operates abnormally or the equipment fails, the relevant equipment or test system triggers the emergency stop signal of the electrical control system, and the emergency stop signal will be transmitted to the fuel system and the engine controller to trigger the emergency stop function; The lubricating oil system exchanges data with the electrical control system through Ethernet, monitors key parameters such as flow and pressure in real time, and implements remote control to provide the vortex electric system with lubricating oil that meets the requirements; The fuel system exchanges data with the electrical control system through Ethernet, monitors key parameters such as flow and pressure in real time, and implements remote control, provides the vortex electric system with fuel that meets the requirements and has an emergency stop function. In emergency conditions, the fuel supply can be quickly cut off within milliseconds; The exhaust system is installed at the exhaust rear end of the vortex electric system to guide the exhaust gas generated by the vortex electric system and guide the cold air flow to prevent the gas from flowing back.

2. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: The engine controller is specifically used for: Receive the load signal and the engine output shaft speed signal. When the load signal is lost instantaneously or the falling slope is too large, and the power turbine output shaft speed is greater than the set value, the emergency stop protection of the turbine engine is triggered.

3. The hybrid power turbine power generation system test bench for aviation according to claim 1, characterized in that: The bench system has margins in both axial and radial directions to compensate for the thermal expansion generated during the eddy-electric system test.

4. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: The turbine engine and generator of the vortex electric system adopt a split structure or an integrated structure. When the integrated structure is adopted, the output end of the turbine engine is directly connected to the generator; when the split structure is adopted, a brake is installed between the turbine engine and the generator. When the vortex electric system loses load in a large state, the transmission shaft speed is directly reduced by the brake, thereby reserving time for the safety measures of the test to take effect.

5. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: The emergency load system includes an emergency load and a switch connected to the emergency load and the generator controller circuit respectively. When a fault occurs in the generator controller, the load absorption system or between the two, causing the vortex electric system to lose load instantly, the switch switches from the load absorption system to the emergency load within milliseconds.

6. The aviation hybrid power turbine power generation system test bench according to claim 5, characterized in that: The emergency load is located on the AC circuit and adopts an air-cooled AC load, an air-cooled DC load with a rectifier, a water-cooled AC load, a water-cooled DC load with a rectifier, an electric dynamometer, an eddy current dynamometer or a grid-connected load.

7. The aviation hybrid power turbine power generation system test bench according to claim 5, characterized in that: The emergency load is consistent with the load of the load absorbing system; Alternatively, the emergency load is set with a predetermined margin compared to the load size of the load absorbing system.

8. The aviation hybrid power turbine power generation system test bench according to claim 5, characterized in that: The switch includes an IGPT switching normally open switch and an IGPT switching normally closed switch, and the IGPT switching normally open switch and the IGPT switching normally closed switch are respectively connected to the emergency load and the generator controller to form an interlocking relationship.

9. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: The fuel system is equipped with a fire damper on the fuel supply pipeline and an external emergency stop oil valve on the fuel supply pipeline of the turbine engine. Its emergency stop signal is connected with the electrical control system through a circuit. Under emergency conditions, the fuel supply can be quickly cut off within milliseconds.

10. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: The exhaust system is movable in the axial direction to adapt to vortex electric systems of different sizes.

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