A test bench for an aviation hybrid turboelectric power generation system

Abstract

The present application discloses a test bench for an aviation hybrid turboelectric power generation system, which includes a 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. The present application properly solves the problems faced by existing turboelectric power systems during tests, effectively reduces test risks, improves test reliability, and can be used for the overall machine test of aviation hybrid turboelectric power systems; the present application uses special protection settings of the engine controller, brakes, and emergency load systems to avoid the risk of runaway caused by load loss during tests of high-speed and high-power turboelectric power systems from three aspects: fuel control, mechanical braking, and emergency load switching. A variety of safety protection measures guarantee each other and act simultaneously; the present application relies on an independently arranged lubricating oil system to solve the requirements for lubrication and cooling of the generator and cooling of the generator controller during tests of turboelectric power systems, ensuring the correct and safe operation of the test bench.

Description

Technical Field

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

[0002] Compared with traditional aero-engine tests, the tests of an aviation hybrid power turbine power generation system (referred to as the turbogenerator system) need to consider the lubrication and cooling of high-power density generators, the cooling of generator controllers (rectifiers), the load consumption of large voltages and large currents, and the safety issues such as the engine running away caused by the instantaneous load loss. When necessary, the on-site assembly problems of the turbogenerator system also need to be considered. Existing engine test benches and turbogenerator system test benches, such as common similar turbogenerator system test benches, are mainly used for generating sets or marine power. There are significant differences in their volume, weight, power-to-weight ratio, and working characteristics from those of aviation hybrid power turbogenerator systems. The design and application of the corresponding test benches are also very different and are not suitable for the tests of aviation hybrid power turbogenerator systems, and cannot completely avoid the risk of engine running away during turbogenerator system tests. In addition, the protection logic of traditional aero-engine controllers generally sets threshold protection for specific parameters. For example, when the speed exceeds a certain limit value, the engine is controlled to stop. For the engine controller, the load parameters are mostly indirect values (obtained by calculation after calibration) and generally are not connected to the protection logic. In the tests of the turbogenerator system, due to generator failures resulting in load loss, the existing protection settings that solely rely on engine speed overrun may cause untimely fuel cut-off and engine running away. Summary of the Invention

[0003] This application provides a test bench for an aviation hybrid power turbine power generation system to solve the technical problems that the existing technology is not suitable for the tests of aviation hybrid power turbogenerator systems and cannot completely avoid the risk of engine running away during turbogenerator system tests.

[0004] This application is realized through the following solutions:

[0005] A test bench for an aviation hybrid power turbine power generation system, comprising:

[0006] A bench system for supporting the operation of the turbogenerator system. The turbogenerator 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;

[0007] An emergency load system, which is connected to the turbogenerator system and the generator controller through cables respectively, and is used for switching the normal load circuit to the emergency load circuit within milliseconds when the turbogenerator system instantaneously loses the load;

[0008] The load absorption system consists of multiple DC resistive dry load cabinets, which are connected to the generator controller circuit and are used for normal loading and absorbing the output electric power of the turbogenerator system.

[0009] The test system measures and collects the operating parameters of the turbogenerator system through test cables, and conducts real-time data exchange 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.

[0010] The electrical control system receives instructions through the operating system, uses the PLC as the central processor, adopts a distributed I / O architecture, and realizes the input and output of engine control instructions and data acquisition functions through DI, DO, AI, AO, and communication module components. It conducts data exchange with the generator controller, emergency load system, load absorption system, lubricating oil system, and fuel system through the real-time Ethernet using the PROFINET protocol, thereby realizing the control of the turbogenerator system and the test bench equipment; while giving the loading power of the load absorption system, it sends a signal to the engine controller to form the linkage between the turbogenerator system and the load absorption system; at the same time, it conducts data exchange with the test system; in case of emergency, when the operation of the turbogenerator system is abnormal or equipment failure occurs, the relevant equipment or the test system triggers the emergency stop signal of the electrical control system, and this emergency stop signal will be transmitted to the fuel system and the engine controller to trigger the emergency stop function.

[0011] The lubricating oil system conducts data exchange with the electrical control system through Ethernet, monitors key parameters such as flow rate and pressure in real time, and realizes remote control to provide qualified lubricating oil for the turbogenerator system.

[0012] The fuel system conducts data exchange with the electrical control system through Ethernet, monitors key parameters such as flow rate and pressure in real time, and realizes remote control to provide qualified fuel for the turbogenerator system and has an emergency stop function. Under emergency conditions, it can quickly cut off the fuel supply within milliseconds.

[0013] The exhaust system is installed at the rear end of the exhaust of the turbogenerator system and is used to discharge the exhaust generated by the turbogenerator system and eject cold air flow to prevent gas reflux.

[0014] Furthermore, the engine controller is specifically used for:

[0015] Receiving 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, it triggers the emergency stop protection of the turbofan engine.

[0016] Furthermore, the test bench system has margins in both the axial and radial directions to compensate for the thermal expansion generated during the test of the turbogenerator system.

[0017] Further, the turbine engine and the 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 the load under large conditions, the rotational speed of the transmission shaft is directly reduced through the brake, leaving time for the safety measures of the test to take effect.

[0018] Further, the emergency load system includes an emergency load and a switcher circuit-connected to the emergency load and the generator controller respectively. When a failure occurs in the generator controller, the load absorption system, or both, resulting in the instantaneous loss of the load of the vortex electric system, the switcher switches from the load absorption system to the emergency load within milliseconds.

[0019] Further, 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, a dynamometer, an eddy current dynamometer, or a grid-connected load.

[0020] Further, the emergency load is the same size as the load of the load absorption system;

[0021] Or,

[0022] The emergency load is set with a predetermined margin compared to the load of the load absorption system.

[0023] Further, the switcher includes an IGPT switching normally open switch and an IGPT switching normally closed switch. 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.

[0024] Further, the fuel system installs a fire damper on the fuel supply pipeline and externally installs an emergency stop fuel valve on the fuel supply pipeline of the turbine engine. Its emergency stop signal is circuit-connected to the electrical control system. Under emergency conditions, the fuel supply is quickly cut off within milliseconds.

[0025] Further, the exhaust system can move axially to adapt to vortex electric systems of different sizes.

[0026] Compared with the prior art, the present application has the following beneficial effects:

[0027] The present application provides a test bench for an aviation hybrid turbogenerator system. The test bench for the aviation hybrid turbogenerator system includes a 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. Starting from the overall design, through the coordinated adjustment and control of multiple process systems of the test bench, the present application properly solves the problems faced by the turbogenerator system during the test, effectively reduces the test risk, improves the test reliability, can be used for the overall machine test of the aviation hybrid turbogenerator system, and provides equipment support for the development of aviation hybrids; the load of the present application is essentially a distributed load cabinet operating in parallel, and the load size can be changed by changing the number of load cabinets to adapt to the test of turbogenerator systems with different powers; the present application uses special protection settings of the engine controller, brakes, and emergency load system to avoid the risk of runaway caused by load loss during the test of high-speed and high-power turbogenerator systems from three aspects: fuel control, mechanical braking, and emergency load switching. Multiple safety protection measures guarantee each other and act simultaneously; the present application relies on the independently set lubricating oil system to solve the requirements for lubrication and cooling of the generator and cooling of the generator controller during the test of the turbogenerator system, ensuring the correct and safe operation of the test bench; the present application monitors and controls the status of all equipment on the test bench, including the test piece, through the test system and the electrical control system, with a high degree of automation.

[0028] In addition to the purposes, features, and advantages described above, the present application has other purposes, features, and advantages. The following will refer to the drawings to further elaborate on the present application in detail. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The schematic embodiments and descriptions thereof of the present application are used to explain the present application and do not constitute an improper limitation to the present application. In the drawings:

[0030] Figure 1 is a schematic diagram of the composition modules of the test bench for the aviation hybrid turbogenerator system according to the preferred embodiment of the present application.

[0031] Figure 2 is a schematic diagram of the test principle of the test bench for the aviation hybrid turbogenerator system according to the preferred embodiment of the present application.

[0032] Figure 3 is a schematic diagram of the composition modules of the test bench for the aviation hybrid turbogenerator system according to another preferred embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0033] The following will elaborate on the embodiments of the present application in detail with reference to the drawings. However, the present application can be implemented in many different ways defined and covered by the following.

[0034] AsFigure 1 As shown in the figure, a test bench for an aviation hybrid turbine power generation system according to a preferred embodiment of the present application includes a 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, where:

[0035] The bench system is used to support the operation of the turbogenerator system. The turbogenerator 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. Among them, the turbine engine and the generator of the turbogenerator system adopt a split structure, and a brake is installed between the turbine engine and the generator. In the initial stage of research and development, especially considering the instantaneous loss of load caused by a generator failure in extreme cases, it is necessary to consider adding a final mechanical braking safety protection measure for the turbogenerator system. Therefore, in this embodiment, when conducting tests on the split turbogenerator system, a brake is installed between the engine and the generator. When the turbogenerator system loses load under large operating conditions, the brake works accordingly at the same time, directly physically reducing the rotational speed of the transmission shaft and buying time for the emergency response of the test personnel or other protection settings. For the turbogenerator system within the rotational speed and power margin of the brake, it is even possible to achieve a complete braking effect relying on the brake. Due to the requirements for response time and applicable power of such brakes, magnetic powder brakes are mostly selected;

[0036] The emergency load system is connected to the turbogenerator system and the generator controller through cables respectively, and is used to switch the normal load circuit to the emergency load circuit within milliseconds when the turbogenerator system loses load instantaneously;

[0037] The load absorption system is composed of multiple DC resistive dry load cabinets, and is connected to the generator controller circuit, and is used for normal loading and absorbing the output electric power of the turbogenerator system. The load absorption system is used for normal loading and absorbing the output electric power of the turbogenerator system; the load absorption system is composed of multiple DC resistive dry load cabinets; the load absorption system has perfect protection functions, anti-interference ability, and high insulation strength; the load absorption system needs to work for a long time and is installed in an outdoor environment with ventilation and heat dissipation conditions.

[0038] The test system measures and collects the operating parameters of the turbogenerator system through test cables, and conducts real-time data exchange with the engine controller, the generator controller, and the electrical control system through Ethernet. The operating states, real-time data, and alarm states of each subsystem of the test bench are centrally and remotely monitored on the display terminal of the test system;

[0039] The electrical control system receives instructions through the control system, uses the PLC as the central processor, adopts a distributed I / O architecture, and realizes the input / output of engine control instructions and data acquisition functions through DI, DO, AI, AO, and communication module components. It exchanges data with the generator controller, emergency load system, load absorption system, lubricating oil system, and fuel system through the real-time Ethernet of the PROFINET protocol, thereby realizing the control of the turbogenerator system and test bench equipment; while giving the loading power of the load absorption system, a signal is sent to the engine controller to form a linkage between the turbogenerator system and the load absorption system; at the same time, data is exchanged with the test system; in case of emergency, when the operation of the turbogenerator system is abnormal or equipment failure occurs, the relevant equipment or test system triggers an emergency stop signal of the electrical control system, and this emergency stop signal will be transmitted to the fuel system and the engine controller to trigger the emergency stop function;

[0040] The lubricating oil system exchanges data with the electrical control system through Ethernet, monitors key parameters such as flow rate and pressure in real time, and realizes remote control to provide lubricating oil that meets the requirements for the turbogenerator system;

[0041] The fuel system exchanges data with the electrical control system through Ethernet, monitors key parameters such as flow rate and pressure in real time, and realizes remote control to provide fuel that meets the requirements for the turbogenerator system. The fuel system has an emergency stop function. A fire damper is installed on the fuel supply pipeline, and an emergency stop fuel drain valve is externally installed on the fuel supply pipeline of the engine body. Its emergency stop signal is connected to the electrical control system through a hard wire. Under emergency conditions, the fuel supply can be quickly cut off within milliseconds, faster than the engine body stop valve controlled by the engine controller;

[0042] The exhaust system is installed at the rear end of the exhaust of the turbogenerator system, and is used to discharge the exhaust gas generated by the turbogenerator system and eject cold air flow to prevent gas reflux.

[0043] This embodiment provides a test bench for an aviation hybrid turbogenerator system. The test bench for the aviation hybrid turbogenerator system includes a 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 bench system supports the operation of the turbogenerator system. The generator of the turbogenerator system converts the mechanical energy of the turbine engine into electrical energy, outputs it in the form of alternating current, and after passing through the emergency load system, is rectified and converted into direct current by the generator controller, and then is absorbed and consumed by the load absorption system to realize the conversion of mechanical energy - electrical energy - thermal energy.

[0044] Starting from the overall design, the test bench for the aviation hybrid turboelectric power generation system in this embodiment properly solves the technical problems faced by the turboelectric system during the test through the coordinated adjustment and control of multiple process systems of the test bench, effectively reduces the test risk, improves the test reliability, and can be used for the overall machine test of the aviation hybrid turboelectric system, providing equipment support for the research and development of aviation hybrid power. The test bench for the aviation hybrid turboelectric power generation system in this embodiment adapts to the tests of turboelectric systems with different powers by changing the capacity of the load absorption system. The test bench for the aviation hybrid turboelectric power generation system in this embodiment uses the special protection settings of the engine controller, the brake, and the emergency load system to avoid the risk of engine runaway caused by load loss during the tests of high-speed and high-power turboelectric systems from three aspects: fuel control, mechanical braking, and emergency load switching. A variety of safety protection measures guarantee each other and act simultaneously. The test bench for the aviation hybrid turboelectric power generation system in this embodiment relies on the independently set lubricating oil system to solve the requirements for the lubrication and cooling of the generator and the cooling of the generator controller during the test of the turboelectric system, ensuring the correct and safe operation of the test bench. The test bench for the aviation hybrid turboelectric power generation system in this embodiment monitors and controls the status of all equipment on the test bench, including the test piece, in real time through the test system and the electrical control system, with a high degree of automation.

[0045] Specifically, in the preferred embodiment of the present application, the engine controller is specifically configured to:

[0046] Receive the load signal and the engine output shaft speed signal, and trigger the emergency stop protection of the turbine engine when the load signal is instantaneously lost or the slope of the decline is too large, and the power turbine output shaft speed is greater than the set value.

[0047] In this embodiment, compared with the limit value control protection of traditional aeroengine tests, the engine controller needs to be specially set to avoid the risk of engine runaway during the test of the turboelectric system. As Figure 2 shown, the engine controller receives the load signal and the engine output shaft speed signal, and can trigger the stop protection of the engine body when the load signal is instantaneously lost or the slope of the decline is too large, and the power turbine output shaft speed is greater than the set value (non-traditional high-speed limit threshold). Among them, the load signal directly comes from equipment such as the load absorption system, which is faster and more accurate in response compared to the load signal collected and calculated by the engine controller itself.

[0048] Preferably, the test bench system has margins in both the axial and radial directions to compensate for the thermal expansion generated during the test of the turboelectric system, preventing the generation of internal stress due to heat during the test and affecting the stability and reliability of the test bench.

[0049] Preferably, the emergency load system includes an emergency load and a switcher that is circuit-connected to the emergency load and the generator controller respectively. When a fault occurs in the generator controller, the load absorption system, or both, resulting in an instantaneous loss of load in the turbogenerator system, the switcher switches from the load absorption system to the emergency load within milliseconds. During the test, if a fault occurs in the generator controller, the load absorption system, or both, causing an instantaneous loss of load in the turbogenerator system, the emergency load system can apply the emergency load within milliseconds, effectively reducing the runaway risk faced during the test of the high-speed and high-power turbogenerator system. The principle is that when the electrical control system determines that the fault condition is established, the switcher switches the normal load circuit to the emergency load circuit; since the emergency load system is on the AC circuit, the emergency load usually selects an AC load.

[0050] Specifically, the emergency load is located on the AC circuit and uses 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, a dynamometer, an eddy current dynamometer, or a grid-connected load.

[0051] Specifically, the emergency load is the same size as the load of the load absorption system, avoiding fluctuations during load switching and ensuring that the turbine blade speed remains the same as before switching when the load is lost.

[0052] Or,

[0053] A predetermined margin is set for the emergency load compared to the load size of the load absorption system to ensure a certain design redundancy and improve the safety of the system.

[0054] Preferably, the switcher 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 and form an interlocking relationship.

[0055] IGBT is a power device with a tube voltage drop and generates a large amount of heat when passing a large current. Therefore, heat dissipation treatment needs to be carried out on the IGBT module, using the method of aluminum heat sinks. The IGBT module is fixed on the aluminum heat sink. To effectively spread the heat and increase the contact reliability, thermal grease is applied to the contact surface between the IGBT module and the heat sink, and then air-cooling treatment is carried out through a fan. Each input and output is led out to the input and output ports through cables. Since there are many IGBTs and the current is relatively large, the main circuit and the secondary circuit are each divided into 2 parts, and each part is switched by a three-phase switch. In this way, each part consists of 6 IGBTs and 1 heat sink, and a total of 24 IGBTs are fixed on 4 heat sinks.

[0056] The switch of this embodiment uses an IGPT as the switching switch, which has a simple structure and is convenient to control, thus ensuring that the action time of the switch during load switching reaches the nanosecond level to avoid test accidents of turbine blade breakage 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 interlock relationship, it also avoids the mis-switching of the load absorption system and the emergency load system, ensuring the reliability and safety of load switching.

[0057] Preferably, the switch includes a normally open high-power solid-state relay and a normally closed high-power solid-state relay. 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 interlock relationship.

[0058] The switch of this embodiment uses a high-power solid-state relay as the switching switch, which has the advantages of high reliability, high life, high sensitivity, small control power, good electromagnetic compatibility, fast conversion, and small electromagnetic interference. Thus ensuring that the action time of the switch during load switching reaches the nanosecond level to avoid test accidents of turbine blade breakage 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 interlock relationship, it also avoids the mis-switching of the load absorption system and the emergency load system, ensuring the reliability and safety of load switching.

[0059] Preferably, the fuel system has an emergency stop function. It installs a fire valve on the fuel supply pipeline and externally installs an emergency stop fuel valve on the fuel supply pipeline of the turbine engine. Its emergency stop signal is connected to the electrical control system through a circuit. Under emergency conditions, within milliseconds, it quickly cuts off the fuel supply, faster than the stop valve of the turbine engine. The fuel system exchanges data with the electrical control system through Ethernet, monitors key parameters such as flow rate and pressure in real time, and realizes remote control.

[0060] Preferably, the exhaust system can move axially to adapt to different sizes of the turbogenerator system.

[0061] As Figure 2As shown in the figure, during the test run of the above embodiment, the special protection settings of the engine controller, the brake, and the emergency load system are used to avoid the risk of engine runaway caused by load loss during the high-speed and high-power turboelectric system test from three aspects: fuel control, mechanical braking, and load switching. A variety of safety protection measures support each other and act simultaneously; at the same time, the independent lubricating oil system solves problems such as the lubrication and cooling of the generator and the cooling of the generator control; the test bench system can be quickly modified modularly to adapt to the installation and support problems of integrated or split turboelectric systems; at the same time, through the test system and the electrical control system, the status of all equipment on the test bench, including the test piece, is monitored and controlled in real time.

[0062] As Figure 3 shown, different from the above-described embodiment, in this embodiment, the turbine engine and the generator of the turboelectric system adopt an integrated structure, and the output end of the turbine engine is directly connected to the generator, with a compact structure, so as to meet the test run requirements of the integrated turboelectric system.

[0063] A test bench for an aviation hybrid turbine power generation system in the above embodiment can be modified modularly to be applicable to the tests of both split and integrated turboelectric systems. The split turboelectric system, as a transition during the development of the integrated turboelectric system, has the advantage that it can enter the test verification at a lower cost and in a shorter time, while its disadvantage is that the technical maturity of the high-power density generator is insufficient, and it is extremely easy to have a runaway accident caused by a generator body failure.

[0064] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications once they know the basic creative concept. Therefore, the appended claims are intended to be interpreted to include the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0065] 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 equivalent technologies, the present application also intends to include these modifications and variations.

Claims

1. A test bench for an aviation hybrid turboelectric power generation system, characterized in that, include: A test bench system is used to support the operation of the vortex electric system. The vortex 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 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. When the vortex electric system loses load in a large state, the transmission shaft speed is directly reduced by the brake, which reserves time for the safety measures of the test to take effect and buys time for the emergency response of the test personnel or other protection devices; 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 via Ethernet, monitors key flow and pressure parameters in real time, and implements remote control, provides the turbo-electric system with fuel that meets the requirements and has an emergency stop function. In an emergency, the fuel supply can be quickly cut off within milliseconds. The fuel system is equipped with a fire damper on the fuel supply pipeline and an external emergency stop valve on the oil supply pipeline of the turbine engine. Its emergency stop signal is connected to the electrical control system through a circuit hardline. In an emergency, the fuel supply can be quickly cut off within milliseconds. An exhaust system, installed at the rear end of the exhaust of the turbogenerator system, is used to discharge the exhaust gas and entrained cold air flow generated by the turbogenerator system and prevent the backflow of combustion gas.

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

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

4. The test bench for the aviation hybrid power turbine power generation system according to claim 1, characterized in that, The emergency load system includes an emergency load and a switcher that is circuit-connected to the emergency load and the generator controller respectively. When a failure occurs in the generator controller, the load absorption system, or both, resulting in an instantaneous loss of load in the turbogenerator system, the switcher switches from the load absorption system to the emergency load within milliseconds.

5. The test bench for the aviation hybrid power turbine power generation system according to claim 4, characterized in that The emergency load is located on the AC circuit and uses 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, a dynamometer, an eddy current dynamometer, or a grid-connected load.

6. The test bench for the aviation hybrid power turbine power generation system according to claim 4, characterized in that, The emergency load has the same load size as the load absorption system; Or, The emergency load is set with a predetermined margin compared to the load size of the load absorption system.

7. The test bench for the aviation hybrid power turbine power generation system according to claim 4, characterized in that, The switcher includes an IGPT switching normally open switch and an IGPT switching normally closed switch. 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.

8. The test bench for the aviation hybrid power turbine power generation system according to claim 1, characterized in that, The exhaust system can move axially to adapt to turbogenerator systems of different sizes.

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